s' UNITED STATES ARMY · 2017-07-22 · 7> co »a i £ (s-cu^ ftfj fm 101-20 field manual •¡s' united states army aviation planning manual return to the army library room 1a518

7> Co »A I £ (S-CU^ ftfj FM 101-20

FIELD MANUAL

•¡s' UNITED STATES ARMY

AVIATION PLANNING

MANUAL

RETURN TO THE ARMY LIBRARY ROOM 1A518 PENTAGON / WASHINGTON, D.C. 20310

\

HEADQUARTERS, DEPARTMENT OF THE ARMY

JANUARY 1979

1

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FM 10120

FOREWORD

This manual is published in accordance with the provisions of AR 95-70 and contains official U.S. Army aviation factors data in a single-source document to be used as a planning guide ONLY. The factors, when used with other Army program documents (e.g., Army Materiel Plan and Materiel Annex Part II to 5 Year Force Structure and U.S. Army Aircraft Standard Avionics/Surveillance Configuration, 5 Year Plan Requirement), will assist commanders, planners, and programmers in establishing a basis for operational, logistical, materiel, personnel, estimates, and the cost requirements for combat readiness of all types and models of Army aircraft. In the event such Army program documents, as mentioned above, indicate later revision, such revisions will take precedence. The data may be used in the preparation of estimates by major commands (theater, field army, or equivalent) but will not be used as a basis of reporting cost or other data.

These planning factors were developed from diversified operational and logistical statistical data and were obtained from various Department of the Army staff offices arid other Army agencies having primary responsibilities for the specific mission activities or related functions.

This manual is published in looseleaf form to facilitate insertion of revisions, changes, and/or additions. Each set of published planning factors will be revised annually to ensure current and accurate data, as well as provide additional factors of interest. DARCOM is responsible for coordinating pertinent planning factors with the appropriate Army staff agency.

Users of this manual are encouraged to submit recommended changes or comments to improve the manual. Comments should be keyed to the specific page, paragraph, and line of the text. Reasons should be provided for each comment to ensure understanding and full evaluation. Com- ments should be forwarded direct to Headquar- ters, U.S. Army Materiel Development and Readiness Command, Directorate for Develop- ment and Engineering, Attn: DRCDE-D, Alexandria, Va., 22333.

Distribution of this Department of the Army publication to Active Army, National Guard, and United States Army Reserve units is by formula distribution and pinpoint distribution methods. Other DOD agencies should request copies required from the Adjutant General, Washington, D.C. Under provisions of Army Regulation 310-1, Military Publications, normal publications supply channels should be followed.

Requests from agencies outside of DOD will be forwarded to The Adjutant General, Washington, D.C. 20315.

Abbreviations used in this manual are listed in AR 310-50 (Standard abbreviations) or Mili- tary standard 12C (Non standard abbreviations).

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* FM 101-20

FIELD MANUAL

NO. 101-20

HEADQUARTERS DEPARTMENT OF THE ARMY

Washington, D. C. , 3 January 1979

UNITED STATES ARMY

AVIATION PLANNING MANUAL

REPORTING ERRORS AND RECOMMENDING IMPROVEMENTS

You can help improve this manual. If you find any mistake or if you know of a way to improve the procedures, please let us know. Mail your letter, DA Form 2028 (Recommended Changes to Publications and Blank Forms), or DA Form 2028-2 located in the back of this manual direct to: Commander, U. S. Army Troop Support & Aviation Materiel Readiness Command, ATTN: DRSTS-MTPS, 4300 Goodfellow Boulevard, St. Louis, MO 63120. A reply will be furnished directly to you.

Table of Contents

Page Forward i Designation of Army Aircraft iv Aircraft Type Classification viii

Chapter 1. OPERATIONS Section I. Aircraft authorization 1-1

II. Flying hour program 1-11 III. Replacement Factors (Attrition) 1-13

IV Standard aircraft characteristics 1-14

Chater 2. LOGISTICS AND MATERIEL Section I. Maximum allowable operating time (MAOT) (major components) 2-1

II. Aircraft equipment 2-2 III. Ferrying and shipping 2-122 IV. Tools 2-128 V. Inspections 2-135

VI. Fuel and oil 2-136 VII. Maintenance man-hours 2-141

VIII. Maintenance categories 2-148

Chapter 3. PERSONNEL REQUIREMENTS Section I. Officer/warrant officer aviation personnel requirements 3-1

II. Enlisted aviation maintenance personnel requirements 3-2

Chapter 4. COSTS Section I. Army aircraft direct costs per flying hours 4-1

II. Aircraft unit flyaway costs 4-4 III. Avionics cost ^ 4-6 IV. Armament cost 4-6

Chapter 5. RESEARCH AND DEVELOPMENT OF MATERIEL 5-1

APPENDIX A REFERENCES A-l

INDEXx Index-1

This manual supersedes FM 101-20, 27 February 1976.

in

FM 101-20

DESIGNATION OF ARMY AIRCRAFT (ROTARY WING)

PRE FERREO

POPULAR NAME AND TYPE

COMBAT ACCEPT SUBST

FOLLOW-ON AIRCRAFT

AH-1G TH-1G

COBRA

ATTACK HELICOPTER

UH-1B UH-1C UH-1M

YAH-64A

l/

V/

CH-47A/B/C

CHINOOK

CARGO TRANSPORT HELICOPTER

YCH-47D

CH-54A/B

TARHE

CARGO TRANSPORT HELICOPTER

OH-6A OH-58 A/C

CAY USE

A/9 "

KIOWA

& an is

LIGHT OBSERVATION HELICOPTER

UH-1D/H EH-1H EH-1X

IROQUOIS

UH-1B

UTILITY HELICOPTER

UH-60A EH-60A

TH-55A

OSAGE

TRAINER HELICOPTER

OFF-THE- SHELF

AV 010094

FM 101-20

7 /

DESIGNATION OF ARMY ARICRAFT (ROTARY WING) CONT’D.

PRE- FERRED

UH-60A EH-60 A EH-60B

YAH-64A

UH-1B/C/M

AH-1S

POPULAR NAME ANDTYPE

BLACK HAWK

UTILITY HELICOPTER

AAH

ATTACK HELICOPTER

IROQUOIS

UTILITY HELICOPTER

COBRA

ATTACK HELICOPTER

COMBAT ACCEPT SUBST

EH-1X

UH-1B UH-1C UH-1M

FOLLOW-ON AIRCRAFT

YAH-64A

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1 FM 101-20

DESIGNATION OF ARMY AIRCRAFT (FIXED WING) (Cont.)

PRE- ’ POPULAR NAME FERREO AND TYPE

COMBAT ACCEPT SUBST

FOLLOW-ON AIRCRAFT

SEMINOLC

U-8D/F/G RU-8D

UTIL ITY AIRPLANE

U-10A

COURIER

UTILITY AIRPLANE

U-21A/G RU-21A D/H

UTE

UTILITY AIRPLANE

MOHAWK

OV-1B/C/D RV-1D

OBSERVATION/SURVEIL- LANCE AIRPLANE

MESCALERO

T-41B OFF-THE-SHELF

TRAINER AIRPLANE

T-42A

COCHISE

OFF-THE-SHELF

TRAINER AIRPLANE

il

AV 010095

vi

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FM 101-20

DESIGNATION OF ARMY AIRCRAFT (FIXED WING) CONT’D.

PRE- FERRED

POPULAR-NAME AND TYPE

COMBAT ACCEPT SUBST

FOLLOW-ON AIRCRAFT

BEAVER

U-6A

. UTILITY AIRCRAFT

AERO COMMANDER

U-9C

UTILITY AIRCRAFT

HURON.

C-12A RU-2ÍJ

CARGO AIRCRAFT

UV-18A

TWIN OTTER

UTILITY STOL AIRCRAFT

U-1A

OTTER

m

UTILITY AIRCRAFT

U-21F RU-21B, C

UTE

. UTILITY AIRCRAFT

Source: DRSTS-MT

vii

FM 101-20 1

Army Aircraft Type Qassification/Reclassification (TC/R) Schedule (Rotary Wing)

TYPE, MODEL

SERIES (TMS)

Rotary Wing AH-IO (TH-1G) AH-IS CH-47À CH-47B CH-47C CH-54A CH-54B OH-6A OH-58A UH-1B UH-1C UH-1D UH-1H UH-1M TH-5SA TH-1G OH-58C EH-1H YCH-47D UH-60A UH-1V EH-1X YAH-64A

CURRENT TYPE

TCC-LCC

S-A S-A

S-B S-B S-A S-B S-B S-A S-A S-B S-B S-B S-A S-B S-A S-A

D

L-(U) D

S-A S-A S-A

PROPOSED TCC-LCC

C-S

c-s c-s c-s c-s c-s c-s c-s c-s c-s c-s c-s c-s c-s

S-A S-B

FY-Qtr of

Proposed TCC-Lcc

88-1

81- 3 83- 1 84- 3 88-4 90-4 86-4 86-4 80-4 83-4 82- 4 82- 4 83- 4 84- 4

79-1

79-3

REPLACEMENT SYSTEM

AH-1S YAH-64A YCH-47D YCH-47D YCH-47D

OH-58C UH-60A UH-60A UH-60A UH-60A UH-60A UH-60A

EH-60A

Source: DRDAV-EKT

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FM 101-20

Army Aircraft Type Classification/Redassifîcation (TÇ/R) Schedule (FIXED WING)

TYPE, MODEL SERIES (TMS)

CURRENT TCC-LCC

PROPOSED TCC-LCC

FY-QTR

of Proposed TCC-LCC

REPLACEMENT SYSTEM

Fixed Wing

U-8D U-8F

U-8G RU-8D U-10A U-21A U-2IF

11-21G

RU-21A RU-21B RU-2IC RU-21D

RU-21H RU-21J

OV-1B OV-1C OV-1D T-41B T-42A C-12A U-1A U-6A U-9C UV-18A RV-1D

S-B S-B S-B S-B S-B S-A S-A SJA

S-B S-B S-B

S-B

LrU

N-D

S-B S-A S-A

S-B S-A S-A C-F C-S C-S S-A S-A

C-S 0-0 C-S

C-S C-S C-S

C-S C-S

0-0

S-B'

S-A C-S

C-S C-S C-S C-S

0-0

0-0

80-4 80-4 80-4

79-4 834 88-3

92-1 914

80-4

79-2

78-4 •

814

814 904 86-2 85-1 .

78-4 .

78-4

RU-21H

OV-1D

0V-1D

U-21A U-21A U-21A

SOURCE: DRDA V-EKT

FM 101-20 1

LEGEND:

TCC - Type Classification Code

C - Contingency

E - Exempt

L - Limited Procurement

N - Perpetuate only until type classified

O - Obsolete

S - Standard

LCC - Logistic Control Code

A - Items/Systems acceptable for the intended mission

B - Items/Systems acceptable for the intended mission which normally are being replaced through modernization

D - Items/Systems undergoing development which have not qualified for type classification

F - Mission Essential Contingency Items

N - Exempt

O - Obsolete item

S - Contingency items other than Mission Essential Contingency Items that are suitable for training

T - Items classified as Limited Procurement to provide quantities for test

U - All items type classified for Limited Procurement

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CHAPTER 1

OPERATIONS

Section I AIRCRAFT AUTHORIZATIONS

Aircraft authorizations are listed by TOE unit authorizations. The current Major Item Analysis (Data Sheets) contains details concerning authorizations for specific areas or commands. The Basis of Issue (BOI) authorizations are updated to comply with the ARCSAIII evaluation.

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1-1. Basis of Issue -- Aircraft Authorization Per Unit

UNIT TOE TOTAL ACFT LOH AH-1 UH-1 CH-47 CH-54 OV-1B OV-1C OV-1D U-21

ARMORED DIVISION Combat Aviation Battalion

Attack Helicopter Co (2) Cbt Spt Avn Co Division Aviation Co Trans Acft Maint Co

Armored Cavalry Sqdn Air Cavalry Troop

RECAP RECAP

RECAP

17 17-85 17-387 57-57 17-87 55-424 17-105 17-108

170 143 72 23 46

2 27 27

66 56 24

32

10 10

51 42 42

9 9

53 45

6 23 14

2 8 8

INFANTRY DIVISION(MECH)RECAP Combat Aviation Battalion RECAP

Attack Helicopter Co (2) Cbt Spt Avn Co Division Aviation Co. Trans Acft Maint Co

Armored Cavalry Sqdn RECAP Air Cavalry Troop

37 17-85 17-387 57-57 17-87 55-424 17-105 17-108

170 143 72 23 46

2 27 27

66 56 24

32

10 10

51 42 42

9 9

53 45

6 23 14

2 8 8

INFANTRY DIVISION Combat Aviation Battalion

Cbt Spt Avn Co (2) Avn Gen Spt Co Attack Helicopter Co Trans Acft Maint Co

Air Cavalry Sqdn HHT, Air Cav Sqdn Air Cavalry Troop (3)

RECAP RECAP

RECAP

7 57-55 57-57 57-58 17-387 55-89 17-205 17-206 17-208

215 130 46 46 36

2 85

4 81

74 44

32 12

30

30

48 21

21

27

27

93 65 46 14

3 2

28 4

24

AIRBORNE DIVISION Combat Aviation Battalion

Cbt Spt Avn Co (2) Avn Gen Spt Co Attack Helicopter Co Trans Acft Maint Co

Air Cavalry Sqdn HHT, Air Cav Sqdn Air Cavalry Troop

RECAP RECAP

RECAP

57 57-55 57-57 57-58 17-387 55-89 17-275 17-276 17-278

215 130 46 46 36

2 85

4 81

74 44

32 12

30

30

48 21

21

27

27

93 65 46 14

3 2

28 4

24

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FM

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1-1. Basis of Issue--Aircraft Authorization Per Unit (Cont.)


AIRMOBILE DIVISION RECAP Division Artillery RECAP

Aviation Battery Aviation Group RECAP

GS Aviation Co Assault Helicopter Bn (2) RECAP

HHC, Aslt Hel Bn (2) Assault Helicopter Co (6)

Medium Helicopter Bn RECAP HHC, Medium Hel Bn Medium Helicopter Co (2)

Attack Helicopter Bn RECAP HHC, Atk Hel Bn Attack Helicopter Co (3)

Air Cavalry Squadron RECAP HHT, Air Cav Sqdn Air Cavalry Troop (3)

Medical Battalion RECAP HHC, Medical BN

TC Battalion RECAP Trans Acft Maint Co (2)

HHC, Ambl Div Bde (3)

67 6-700 6- 702 7- 200 7-202 7-255 7-256 7- 257

55-165 55-166 55-167 17-385 17-386 17-387 17-95 17-96 17-98

8- 25 8-26

55-405 55-407 67-42

470 19 19

314 26

126 6

120 50

2 48

112 4

108 85

4 81 12 12

4 4

36

122 16 16 52 10

6 6

36

36 30

30

24

90

63

63

63 27

27

210 3 3

151 16

120

120 2 2

13 4 9

24 4

24 12 12

4 4

12

48

48

48

48

AIR CAV CBT BDE RECAP Hq & Hq Troop, ACCB Attack Helicopter Bn (2) RECAP

HHC, Atk Hel Bn (2) Attack Helicopter Co (6)

Air Cavalry Sqdn RECAP HHT, Air Cav Sqdn Air Cavalry Troop (3)

Support Battalion RECAP Trans Acft Maint Co Medium Helicopter Co (Medical Co, ACCB)

17-200 17-202 17-385 17-386 17-387 17-205 17-206 17-208 29-155 55-417 55-167

8-157

336 9

224 8

216 85

4 81 18

2 16

(4)

106 4

72

72 30

30

153

126

126 27

27

61 5

26 8

18 28

4 24

2 2

(4)

16

16

16

M

FM

101-2

0

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1-1. Basis of Issue -- Aircraft Authorization Per Unit (Cont.


ARM UAV REGT HHT, Arm Cav Regt

Air Cavalry Spt Troop Combat Spt Troop

RECAP 17-51 17-52 17-58 17-59

75 19 27 29

29 6

10 13

9

9

37 13 8

16

HHC, Sep Inf Bde HHC, Sep Armd Bde HHC, Sep Inf Bde (MECH) HHC, Sep Abn Bde HHC, Sep Lt Inf Bde

7-102 17-102 37-102 57-102 77-102

11 8 8

11 11

8 6 6 8 8

3 2 2 3 3

Command Airplane Co

Corps Aviation Co

Army Aviation Co

Aviation ATC Unit

HHD Air Traffic Control Gp

Air Traffic Control Bn HHD, ATC Bn

Aslt Spt Hel Co

Aviation Spt Det

Aviation Operating Teams

HHC, Engr Gp

HHC, EngrCmd

HHB, Pershing Bde

RECAP

1-117

1-127

1-137

1-207

1-222

1-225 1-226

1-258

1-277

1-500

5-52

5- 201

6- 604

21

39

41

4

2

3 3

17

11

7

5

16

20

15

5

1

3

2

17

14

3

3 3

1

6

1

4

2

16

16

21

2

12

1

2

FM 101-20

1-1. Basis • • ircraft Authorization Per Unit (Cont.)

UNI TOE TOTAL ACFT LOH AH-1 UH-1 CH-47 CH-54 OV-1B OV-1C OV-1D U-21

Cbt Spt Avn Co

Med Air Ambulance

ArinyCmd SigBn HHD, Army Cmd Sig Bn

Army Area Sig Bn HHC, Army Area Sig Bn

Signal Bn, ABN Corps HHC, Signal Bn ABN

Signal Bn, Cmd Op HHC, Signal Bn, Cmd Op

Attack Helicopter Bn HHC, Attack Hel Bn Attack Helicopter Co (3)

Attack Helicopter Co

HHC, MPGp

Scout Org

MI Co, Aerial Survl

MI Co, Aerial Survl

MI Co. Aerial Survl

MI Det, Aerial Survl

ASA Div Spt Co

ASA Bde Spt Co

Med EVAC Tm RH, Hel Amb

Aerial Exploit Bn Relap

CBTI CO (AS)

EW AVN CO, FWD

RECAP

RECAP

RECAP

RECAP

RECAP

7- 357

8- 137

11-75 11-76

11-85 11-86

11-225 11-226

11-405 11-406

17-385 17-386 17-387

17-387

19- 272

20- 500

30-79

30-88

30-128

30-600

32-57

32-64

8-660

30-105

30-179 30-199

23

25

3 3

1 1

3 3

12 12

112 4

108

36

5

2

18

18

18

6

3

2

6

30

18 12

7 7

36

36

12

5

63

63

21

23

25

1 1

3 3

5 5

13 4 9

3 J-/

2_L/

18 12

6

6

12

24^/

61/

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FM 101-20

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1-1. Basis of Issue -- Aircraft Authorization Per Unit (Cont.)

UNIT

ASA Aviation Co

Medium Helicopter Bn Medium Helicopter Co (3)

Medium Helicopter Co Heavy Helicopter Co

Trans Acft Maint Co

Trans Acft Maint Co

Trans Acft Maint Co

Division (Training)

RECAP

TOE

32-99

'55-165 55-167

55-167 55-259

55-457

55-458

55-459

97

TOTAL ACFT

12

75 75

25 10

2

3

2

2

LOH AH-1 UH-1

3 3

1 1

2

2

2

1

CH-47

72 72

24

CH-54 OV-1B OV-1C OV-1D

6 A/

U-21

6 A/

J_/ EH-1 Acft

2_/ RU or RV Acft

3/ 6EA RV-1D & 18 EA OV-1D

Source: DRSTS-SPME

FM 101-20

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FM 101-20

1-2. Test and Test Support Aircraft.

Requirements for test and test support aircraft are established as follows:

a. All plans of test or research/development programs which require the use of aircraft for any phase will identify the specific type of aircraft required and the purpose (e.g., competitive evaluation of navigation aids in utility helicopter, air transportability of missile in cargo helicopter).

b. The agency providing test service to customers normally requires one aircraft to support two plans of test, with the following exceptions:

(1) An aircraft which is on bailment for an extended period cannot be considered as an available asset to fill additional requirements.

(2) An- aircraft which has been modified to a special configuration (flying lab, armament test bed) in support of a particular specialized long range R & D program may not be considered as a suitable available asset to apply against normal test and test support aircraft requirements during a given fiscal year. (How- ever, this aircraft may become available for use in other programs in subsequent years.) Nonstandard aircraft assets shall not be considered as suitable substitutes for Army aircraft when computing test and test support aircraft requirements. Requirements should be based on use of Army-type aircraft to support Army programs. Use of nonstandard aircraft (C-47, T-28) for Army test programs will be authorized only if an Army-type aircraft cannot be made available or is not suitable for the intended purpose.

Example: A USAF jet aircraft may be necessary for missile chase at firing sites.

c. In addition to aircraft originally assigned to support research, development, test, and evaluation, additional aircraft may be allocated, if required, in accordance with revised development/test programs.

1-3. Authorized Aircraft Designations.

a. All Department of Army Aircraft have been assigned designations in accordance with provisions of AR 70-50. Explanation of terms are as follows:

(1) Status prefix symbol. The status symbol (letter), will indicate an aircraft being used for experimentation and special or service test and will be placed at the immediate left of the modified mission symbol, or the mission/type symbol if no modified mission symbol is applicable.

(2) Modified mission symbol. A letter used to indicate the current capability of an aircraft when it is so modified that its original intended capability is no longer applicable, or when it has an added or restricted capability. The modified missioh symbol will consist of a prefix letter placed at the immediate left of the basic mission or type symbol. Only one modified mission symbol will be used in any one designation.

(3) Basic mission symbol. A letter used to indicate the basic intended function or capability of the aircraft, such as observation, utility, etc.

(4) Type symbol. An additional letter which designates helicopter and V/STOL aircraft. An aircraft identified by a type symbol, such as “H” for helicopter, will be further identified by only one mission symbol whether it be basic mission of a modified mission symbol. (A basic mission or type symbol, once officially assigned, will not be changed without the approval of the Assistant Secretary of Defense (Instal- lation and Logistics).

(5) Design number. The sequence number of each new design of the same basic mission or type aircraft. A number will be assigned consecutively for each basic mission or type. New design numbers will be assigned when an existing aircraft is redesigned to an extent that it no longer reflects the original configuration or capability.

(6) Series letter. A letter used to denote differences affecting the relation of the vehicle to its ground environment, and major modifications to the aircraft which result in significant changes to its logistic support. A letter will be assigned to each series change of a specific basic design. In designing new aircraft, the series letter will be in consecutive order

1-7

FM 101-20

starting with the letter “A.” To avoid confusion, the letters “I” and “O” will not be used as series Symbols. (Examples of series symbol change would be. installation of different engines, propellers, extra fuel tank, etc.)

(7) Complete designation. The complete designation shall consist of items (1) through (6) as applicable, in the order shown. A dash (-) will be inserted between the basic mission/type' symbol and the design number.

EXAMPLE: Y U H - 1 A : I

Status Prefix Symbol (Prototype) « ■■ ■ < Basic Mission Symbol (Utility Mission) * - —■—1 i Type Symbol (Helicopter Type) * Design Number (No. Type Helicopter) * ■ ■ " ■ Series Letter (1st Series)-4 : ' —

b. Status prefix symbols (classification letters) are as follows:

LETTER TITLE , DESCRIPTION

G

J

N

X

Permanently Ah aircraft permanently grounded, Grounded ; used for ground instruction and

training.

Aircraft on special test programs by authorized organizations or on bailment contract having a special test configuration or whose installed property has been temporarily removed to accommodate the test. At completion of the test, the vehicle will be returned either to its original configuration or to standard operational configuration.

Special Test, Aircraft on special test programs Permanent ' by authorized activities or on bail-

' ment contract, whose configuration ' is so drastically changed that return

of aircraft to its original configuration or conversion to standard operational configuration is beyond: practicable or economical limits.

t

Experimental Aircraft in a developmental, experimental

stage where basic mission symbol and design number have been designated but not

' established as a standard'vehicle.

Special. Test, Temporary ;

1-8

FM 101-20

LETTER TITLE DESCRIPTION

U’-*

Prototype

Planning

Aircraft procured in limited quantities to develop the potentialities of the design.

Designations used for identification purpose during the planning or pre- development stage.

c. Modified missions symbols (prefix letters) are as follows:


Attack

C

E

Q

R

Cargo/ Transport

Special Electronic Installation

Drone

Reconnaissance

Aircraft modified to search out, attack, and destroy enemy land or sea targets, using conventional or special weapons. Also used for interdiction and close air support mission.

Aircraft modified for carrying cargo and/or passengers.

Aircraft equipped with electronic devices for employment in one or more of the following missions.

(1) Electronic countermeasures ( 2) Airborne early warning radar (3) Airborne command control including

communications relay (4) Tactical data communications link for

all nonautonomous modes of flight.

Aircraft modified to be controlled from a point outside the aircraft.

Aircraft modified and permanently equipped for photographic and/or electronic reconnaissance missions.

U

V

Trainer

Utility

Staff

Aircraft modified and equipped for training purposes.

Aircraft having small payload, modified to perform miscellaneous missions such as carrying cargo or passengers, and towing targets.

Aircraft modified to provide accommodations such as chairs, tables, lounge, and berths for the transportation of staff personnel.

d. Basic mission and type symbols are as follows:


Attack Aircraft designed to search out, attack, and destroy enemy land or sea targets, using conventional or special weapons. Also used for interdiction and close air support missions.

1-9

FM 101-20


C

H

O

R

T

U

V

X

Cargo/ Transport

Helicopter

Observation

Reconnaissance

Trainer

Utility

VTOL and STOL

Research

Aircraft designed for carrying cargo and/or passengers.

A rotary-wing aircraft designed with the capability of flight in any plane; e.g., horizontal, vertical, or diagonal.

Aircraft designed to observe (through visual or other means) and report tactical information concerning composition and disposition of enemy forces, troops, and supplies in an active combat area.

Aircraft designed to perform reconnaissance missions.

Aircraft designed for training personnel in the operation of aircraft and/or related equipment, and having provisions for instructor personnel.

Aircraft used for miscellaneous missions such as carrying cargo and/or passengers, towing targets, etc. These aircraft include those having a small payload.

Aircraft designed for vertical takeoff or landing with no takeoff or landing roll, or aircraft capable of takeoff and landing in a minimum prescribed distance.

Aircraft designed for testing configurations of radical nature. These aircraft are not normally intended for use as tactical aircraft.

e. Application for a special aircraft designa- f- A complete listing of model designations tion or cancellation of a previously authorized assigned to military aircraft is contained in Army designation may be accomplished by addressing AR 70-50.

the request CDR, US Army Materiel Development and Readiness Command, ATTN: DRCDE-D, Alexandria, VA 22333. Application for status prefix symbol “J” (Special Test, Temporary) will be forwarded to CDR, USATSARCOM, ATTN: DRSTS-X(2), St. Louis, MO 63120, providing complete identification, purpose/ justification and length of time required.

1-10

FM 101-20

Section II. FLYING HOUR PROGRAM

The flying hour program can be calculated by taking the average inventory for the command and multiplying it by the annual flying hour rate for the particular aircraft.

Example:

FORSCOM OV-1 - Fiscal year 1975

Average number of aircraft 21 Annual flying hour rate 216 21 X 216 = 4536 hours

Source: DCSOPS—DAMO

1-4. Basic Annual Flying Hour Planning Factors

a. A Worldwide Flying Hour Program is developed annually by the Department of the Army for use in budget preparation and in planning for logistical support of aircraft. It is used as a basis for management of the entire aircraft inventory and is not applicable to the operation of a single aircraft or to the aircraft of any specific aviation unit or activity.

b. The flying hour program for each major command is published annually in Chapter V, Section 4 of the Department of the Army. Program and Budget Guidance Document. This document lists flying hour guidance in bulk flying hours for each type of aircraft assigned to the major commands. Factors considered in development of command flying hour programs include: the projected aircraft inventory, mission requirements of the command, aviator availability.

budgetary limitations, logistical considerations and other variables which may affect aircraft utilization within the commands. The DA Flying Hour Program is not expressed in flying hour rates. An additional factor to be considered in development of command flying hour programs is the aviator training requirement of the new aircrew training manuals (TC1-134 series) as prescribed by AR 95-1.

c. The basic flying hour planning factors contained below are suitable for use in intermediate and long range planning at any level of command. Two points of rationale used in the development of these factors should be considered in planning applications; these are:

(1) Aircraft assigned to TOE units are intended to meet combat requirements. In a peacetime situation or noncombat environment, utilization of these aircraft should be restricted to only that flying time necessary to provide adequate training for aviation units and other units which are supported by aviation units.

(2) Indirect support aircraft are assigned to TDA units and must meet specific administrative, training, or RDTE requirements. Utilization of indirect support aircraft, except training and training support aircraft assigned to the aviation training base and RDTE aircraft, must meet or exceed the planning factors shown, to justify retention in the aircraft inventory at every level of command. Utilization of training base aircraft is determined by the student training rate approved or programmed for the year under consideration. Utilization of RDTE aircraft is basically determined by the requirements of the RDTE programs supported.

1-11

FM 101-20

1-5. Table of Basic Flying Hour Planning Factors 1./

TYPE AIRCRAFT

TOE PEACETIME

(WORLDWIDE) ENVIRONMENT

lAVG MONAVG YR

TOE ACTIVE COMBAT

ENVIRONMENT A VG MON AVG YR

INDIRECT SUPPORT

AIRCRAFT (WORLDWIDE) ALL ENVIRONMENT^/

AVG MON AVG YR U-21 A, F, G OV-1 B, C, D/RV-1D

OH-6 A OH-58 A UH-1 B/C/M UH-1 D/H AH-1 G, S, CH-47 A, B, C CH-54 A. B C12 U-8 D, F, G RU-21 A.B.C.D, H,J EH-1H/EH-1X UH-60A

35 20

20 20 20 25 20 20 15 35 35 35

25 25

420 240

240 240 240 300 240 240 180 420 420 420

300 300

74 58

68 68 55 79 65 58 43 74 74 74

79 76

888 696

816 816 660 948 780 696 516 888 888 888

948 912

35 25

25 25 25 25 25 25 25 35 35 35

25 35

420 300

300 300 300 300 300 300 300 420 420 420

300 420

iAll factors include operational readiness float aircraft.

-£/Does not include training and training support aircraft assigned to the training base, RDTE (test and test support) aircraft, or aircraft type classified contingency.

Source: DCSOPS-DAMO-RQD

1-12

1-6.

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t F

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rs,

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thly

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FM-101-20

Section III. REPLACEMENT FACTORS (ATTRITION)

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1-13

FM 101-20

Comments:

To arrive at average peacetime operational inventory, (standard aircraft only), the following categories were not considered :

a. Combat inventory and losses

b. Maintenance trainers

c. Depot inventory

d. Aircraft in transit

e. Losses due to natural phenomena

f. Losses due to obsolescence

Section IV. STANDARD AIRCRAFT CHARACTERISTICS

Standard aircraft herein will change as

characteristic data contained modifications or additions and

deletions of aircraft components or equipment are made.

Figure 1-1. AH-1G and TH-1G

Will be furnished at a later date —

Figure 1-1A. AH-1S

1-15

1

FM 101-20

DIMENSIONS

10FT4IN

3FT6IN

Rotor dia ‘44 Ft. Length:

Rotors operating 53 Ft.

Fuselage 45 Ft. 2-1/4 In. Span (max

lateral) 10 Ft. 4 In. Height 11 Ft. 7 In.

Tread .' 7 Ft. 4'In. Rotor gnd clear -

anee (static) 7 Ft. 10 In.

10 FT 2 IN

/°\ — 3FT —

—7FT4IN-H

27IN

-'1

a u F

44 FT 6FT 2IN

0/ 70

3.75 IN

7FT 10IN

13FT 6IN

MAXIMUM LENGTH 52 FT 11 IN

ROTORS TURNING 8FT6IN 14FT4IN

10FT4IN

11 FT 7IN

t=dt=il 2FT4.25IN

45FT2.2IN 9 FT 2 IN

1FT 1.25IN

Figure 1-2. Principal Dimensions, AH-1G emd TH-1G

1-16

1-17

1-7. AH-1G/TH-1G* (Hueycobra) Characteristics.

ENGINE MISSION AND DESCRIPTION WEIGHTS

No. and Model (1)‘T53-L-13B

Mfr Lycoming Engine Spec. No 104.33 Type Free Power Turbine

Reduction Gear Ratio 0.3115

Tail Pipe Fixed Area

Augmentation None

ENGINE RATING

SEA LEVEL STD SHP

Military 1400

Normal

RPM MIN

6600 30

1250 6600 Cont.

TECHNICAL PUBLICATIONS

AIRFRAME:

TM55-1500-339-S TM5B-1500-220-PM TM55-1520-221-10 &10CL TM55-1520-221-20 TM55-1520-221-34 TM55-1520-221-23P TM56-1520-221-PMS TM55-1520-221-MTF

ENGINE: TM56-2840-229-24 TM55-2840-229-23P

Mfr’s Model: BeU 209

The primary missions of this aircraft arethoseof an armed tactical helicopter capable of delivering weapons fire, low altitude high speed flight, search and target acquisition, reconnaissance by fire, multiple weapons fire support, and troop helicopter support. The aircraft is capable of performing these missions from prepared or unprepared areas, under day and night VFR conditions within a temperature range of — 250F to +125°F.

The gas turbine powered “Hueycobra” is of compact design featuring tandem seating to give both pilot and gunner nearly unlimited visibility. Both crew stations have flight control and fire control systems permitting flexibility in division of functions under all normal and emergency situations.

A mission designed fuselage coupled with the 540 rotor system gives a low vibration level plus increased maneuverability and speed. Four wing stores stations and an integral chin turret provide a high degree of armament versatility with the capability of quickly changing a wide combination of weapons to match the desired mission. Reliability and maintainability are ensured through the use of many UH-1 parts which have been combat proven.

Other features include a crashworthy fuel system with closed circuit refueling capability, and a tractor tailrotor system.

DEVELOPMENT

Date of contract 4 April 1966 First flight (Similar aircraft) 7 September 1965 First acft delivered 18 September 1966

FEATURES

Advanced flexible gun tunet Armor protection for crew and

critical components. Hardpoints for rockets, and

external stores on wings. Stability Control Augmentation

System (SAS) eliminates stabilizer bar and provides a stable gun platform.

PERSONNEL

Light Scout, Heavy Scout or Hog Mission

Pilot 1 Gunner 1

Ferry Mission Pilot Copilot...

LOADING

Empty

LB.

5809 (Q

Combat Clean Light Scout Heavy Scout Hog

Max. Takeoff Max. Landing

(C) Calculated

8521 (C) 9500 (Q 9500 (Q

9500 (C) 9500 9500

FUEL AND OIL

Fuel: Grade JP-4/5 Spec MIL-T-5624 No. tanks 2 Location Fuselage Qty 26 2 gal

OU: Spec MIL-L-7808/

MIL-L-23699 No. tanks 1 Location Fuselage Qty 3.4 gal

AVIONICS / ARMAMENT

Refer to Chapter 2.

FLYAWAY COSTS / NSN

AH-1G, NSN 1520-00999-5821 LINE K29660, FLYAWAY COST $509,833

♦TH-1G. Addition of Instructor Flight Controls and Instrument Panel converts the AH-1G to the TH-1G.

FM

101-20

1-18

1-8. Loading and Performance — Typical Mission AH-1G and TH-1G

CONDITIONS

TAKEOFF WEIGHT (fo)

Fuel at 6.5 Ibs/gal (Grade JP-4) (Ib)

Payload (lb)

Takeoff Power Loading (lb SHP)

Disk Loading (lb sq ft)

Autorotation Speed (Min R/D) (kn)

Takeoff Ground Run at SL (ft)

Takeoff to Clear 50 ft (ft)

Vertical Rate of Climb at SL (fpm)

Maximum Rate of Climb at SL (fpm)

Speed for Max R/C at SL (kn)

Time. SL to 5000 ft (min)

Time. SL to 10t000 ft (min)

Service Ceiling (100 fpm) (ft)

Absolute Hovering Ceiling (ft)

COMBAT RANGE (nmi) Average Cruise Speed (kn)

Cruising Altitude (Initial) (ft)

Cruising Altitude (Final) (ft) Total Mission Time Chr'i

COMBAT RADIUS

Average Cruise Speed

Cruising Altitude (Outbound)(Min/Max)

Cruising Altitude (Inbound)

Total Mission Time

(nmi)

(kn)

.(ft)

.(ft)

-(hr)

MISSION I LIGHT SCOUT

MISSION II HEAVY SCOUT

MISSION III HOG

MISSION IV

FERRY (CLEAN)

9171

1572

1792

8.34

6.04

65

105

267

1330

64

3.7

8.3

12450

141.1

133

6350/9800

10000

2.4

"■'•1

9500

1277

2416

8.64

6.25

65

127

344

1230

65

4.0

9.2

11420

95.3

125

5350/7250

10000 1.8

',r:

9500

1025

2668

8.64

6.25

65

127

344

1230

65

4.0

9.2

11420

70.1

125

5600/7200

10000 1.4

7671

1672

192

6.97

5.05

65

0 0

1210 1860

60

2.7

5.6

18200

10650

371.1

141

10000 10000

2.7

FM 101-20

1*19

1-8. Loading and Performance — Typical Mission AH-1G and TH-1G (Cont.)

CONDITIONS MISSION I

LIGHT SCOUT

MISSION II

HEAVY SCOUT

MISSION HI

HOG

MISSION IV

FERRY (CLEAN)

COMBAT WEIGHT Combat Altitude Combat Speed Combat Climb Combat Ceiling (500 ft/min) Service Ceiling (100 ft/min) . . Absolute Hovering Ceiling . . .

Takeoff Ground Run at SL . . Takeoff to Clear 50 ft Maximum Rate of Climb at SL Speed for Max R/C at SL . . . Max Speed at SL Basic Speed at 5000 ft . . . .

• -Ob) • -(ft) . (kn) (2) .(fpm) (2) . .(ft) (2)

• -(ft) (2)

••(ft) 0) • -(ft) (1) “

LANDING WEIGHT Ground Roll at SL Total from 50 ft .

• •(ft) 0)2/ .(fpm) (2)3/

• (kn) (2)2/ • (kn) (2) • (kn) (2)2/

.(lb)

• (ft) •(ft)

8148 Sea Level

140 1665

15350 16300 8500

0 0

1665 62

140 142

7413 0 0

7937 Sea Level

137 1745

16250 17100 9450

0 0

1745 61

137 139

7383

0 0

7020 Sea Level

132 2140

20200 21000 13750

0 0

2140 58

132 135

6578 0 0

6231 10000

155 2170

23800 24550 17700

0 0

2490 54

149. 154

6231 0 0

FM 101-20

FM101-20

DIMENSIONS

10 FT 9 IN

3FT6IN

,10 FT 2 IN

Rotor dia 44 Ft. Length:


Fuselage 44 Ft. 9 In. Span (max

lateral) 10 Ft. 9 In. Height 11 Ft. 7 In.

Tread 7 Ft. 4 In. Rotor gnd clear-

ance (static) 7 Ft. 10 In.

3 >

/*°\ 4FT|

-UFTI—

—7 FT 4 IN-1

2 FT 3 IN

a cs □ 44 FT

FT IN 0/ 70

9* f/7

MAXIMUM LENGTH 53 FT

ROTORS TURNING o FT 6 IN 14 FT7IN

10 FT 4 IN 11 IN ♦

4 IN

11 FT7IN

2FT4IN4FT11IN

t 9 FT 2 IN

44 FT 9 N

13FT5IN

7 FT 10 IN

1 FT 1 IN

Figure 1-3. Principal Dimensions AH-IS (mod)

1-20

1-21

1-9. AH-1S (MOD) Characteristics

ENGINE MISSION AND DESCRIPTION WEIGHTS..

Mfr’s Model: Bel 209 LOADING ■ LB.

No. and Model Mfr Engine Spec. No Type Reduction Gear Ratio Tail Pipe Augmentation

(DT53-L-703 Lycoming

104.43 Free Power Turbine 0.3115 Fixed Area None

ENGINE RATINGS

SEA LEVEL STD

Military

Normal

SHIP RPM MIN

1485 6600 30

1300 6600 Cont


AIRFRAME:

TM55-1500-339-5 T55-1500-220-PM TM55-1520-234-10 & 10CL TM55-1520-234-23 TM55-1520-234-MTF TM55-1520-234-23P TM55-1520-234-PMS

ENGINE: TM55-2840-229-24 TM55-2840-247-23P

The primary mission of this aircraft is anti-arbor: providing a stable airborne platform for the tube launched, optically tracked, wire guided missile (TOW) helicopter support. The aircraft is capable of performing this mission from prepared or unprepared areas, under day and night VFR conditions within a temperature range of — 25°F to +125°F.

The gas turbine powered “Cobra TOW” of compact design featuring tandem seating to give both pilot and gunner nearly unlimited visibility. Both crew stations have flight control and fire control systems permitting flexibility in division of functions under all normal and emergency situations.

A mission designed fuselage coupled with the 540 roto system gives a low vibration level plus increased maneuverability and speed. Four wing stores stations and an integral chin turret provide a high degree of armament versatility with the capabihty of quickly changing a wide combination of weapons to match the desired mission. Reliability and maintainability are ensured through the use of many UH-1 parts which have been combat proven.

Empty Combat Clean Scout Light Anti-Armor Heavy Anti-Armor Max Takeoff Max Landing

6,479 (C)

9,364 10,000 9,639 9,975

10,000 10,000

(C) (C) (C) (C)

(C) Calculated

FUEL AND OIL

Fuel: Grade JP-4/5 Spec MIL-T-5624 No. tanks 2 Location Fuselage Qty 262 gal.

OU:

Other features include a crashworthy fuel system with closed circuit refueling capability, and a tractor tailrotor system, TOW missile subsystem and helmet sight fire control subsystem.

DEVELOPMENT

Development Contract Production contract First Prod. Del

FEATURES

Advanced flexible gun turret. Armor protection for crew and


external stores on wings. StabUity Control Augmenta-

tion System (SAS) eliminates stabUizer bar and provides a stable gun platform.

Helmet Sight Subsystem TOW Missile Subsystem

May 1974 Dec. 1974 May 1976

PERSONNEL

Anti-Armor Mission Pilot 1 Co-Pilot/Gunner ... 1

Ferry Mission Klot i 1 Copilot 1

Spec MIL-L-7808/ MIL-L-23699

No. tanks 1 Location Fuselage Qty 3.4 gal.

AVIONICS/ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS / NSN

NSN 1520-00504-9112 Lin K29694 COSTS

$575,000

NOTE: Remainder of AH-1Q Models to be converted to AH-1S Models by December 1978.

FM 101-20

FM 101-20

DIMENSIONS

10 FT 8 IN

3FT6IN.



Fuselage 44 FT 7 In. Span (max

lateral) 10 Ft. 8 In. Height 11 Ft. 7 In. Tread 7 Ft. 4 In. Rotor gnd clear-

ance (static) 7 Ft. 10 In. 9 FT 11 IN. □

4 FT 10 IN

1—7FT4IN—1

> 2 FT 3 IN

a cu u d

44FT FT IN

TO 9*

MAXIMUM LENGTH

7 FT 10 IN.

13 FT 6 IN. 53 FT

ROTORS TURNING 8 FT 6 IN 14 FT7IN

11 N 10’ 6”

4 IN. u O' FT 7IN

a 5 FT 2 FT 4 IN.

44 FT 7 IN. 9 FT 3 IN.

1 FT 1 IN.

Figure 1-4. Principal Dimensions AH-1S (Prod)

1-22

1-23

1-10. AH-1S (Prod) Characteristics


No. and Model Mfr Engine Spec. No Type Reduction Gear Ratio Tail Pipe Augmentation

(1) T53-L-703' Lycoming 104.43

. Free Power Turbine 0.3115 Fixed Area None

ENGINE RATINGS

SEA LEVEL STD

Military

Normal


SHIP RPM MIN

1400 6600 30

1250 6600 Cont.

AIRFRAME: TM55-1500-339-5 TM55-1500-220-PM TM55-1520-236-MTF TM55-1520-236-23P TM55-1520-236-PMS

ENGINE: TM55-2840-229-24 TM55-2840-247-23P

Mfr’s Model: Bel 209

The primary mission of this aircraft is anti-tank, providing a stable airborne platform for the tube launched, optically tracked, wire guided missile (TOW) helicopter support. The aircraft is capable of performing this mission from prepared or unprepared areas, under day and night VFR conditions within a temperature range of -25°F to +125°F.

The gas turbine powered “Cobra-TOW” of compact design featuring tandem seating to give both pilot and gunner nearly unlimited visibility. Both crew stations have flight control and fire control systems permitting flexibility in division of functions under all normal and emergency situations.

LOADING


LB.

6,479 (C)

9,364 (C)

9,639- (C) 9,975 (C)

10,000 10,000

(c) Calculated

A mission designed fuselage coupled with the 540 roto system gives a low vibration level plus increased maneuverability and speed. Four wing stores stations and an integral chin turret provide a high degree of armament versatility with the capability of quickly changing a wide combination of weapons to match the desired mission. Reliability and maintainability are ensured through the use of many UH-1 parts which have been combat proven.

FUEL AND OIL .

Fuel: Grade JP-4/5 Spec MIL-T-5624 No. tanks 2 Location Fuselage Qty 262 gal.

Oil:

Other features include a crashworthy fuel system with closed circuit refueling capability, and a tractor tailrotor system, TOW missile subsystem and helmet sight fire control subsystem.

DEVELOPMENT

Spec MIL-L-7808/ MIL-L-23699

No. tanks 1 Location Fuselage Qty 3.4 gal.

Development Contract Production contract .. First Prod. Del

FEATURES

Advanced flexible gun turret. Armor protection for crew and


external stores on wings. Stability Control Augmenta-

tion System (SAS) eliminates stabilizer bar and provides a stable gun platform.

Helmet Sight Subsystem TOW Missile Subsystem

Jan 1975 Dec 1975 Mar 1977

PERSONNEL

Anti-Armor Mission Pilot 1

Co-Pilot/Gunner 1

Ferry Mission

AVIONICS/ ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS/NSN -

NSN 1520-00504-9112 Lin K29694, COSTS: Refer To Table 4-3, Page 4-4.

Pilot 1 Co-Pilot 1

FNI 101-20

ro »

1-111. Loading and Psrformane© — Typieal Emission ÂH-1S (R/IOD) and (PROD)

CONDITIONS

TAKEOFF WEIGHT (lb) Fuel at 6.5 Ibs/gal (Grade JP-4) (lb) Payload (lb) Takeoff Power Loading (lb SHP) Disk Loading (Ibsqft) Autorotation Speed (Min R/D) (kn) Takeoff Ground Run at SL (ft) Takeoff to Clear 50 ft (ft) Vertical Rate of Climb at SL (fpm) Maximum Rate of Climb at SL (fpm) Speed for Max R/C at SL (kn) Time: SL to 5000 ft (min) Time: SL to 10,000 ft (min) Service Geling (100 fpm) (ft) Absolute Hovering Ceiling (ft)

COMBAT RANGE (nmi) Average Cruise Speed (kn) Cruising Altitude (Initial) (ft) Cruising Altitude (Final) (ft) Total Mission Time (hr)

COMBAT RADIUS (nmi) Average Cruise Speed (kn) Cruising Altitude (Outbound) (Min/Max)..(ft) Cruising Altitude (Inbound) (ft) Total Mission Time (hr)

MISSION I SCOUT

10,000 1,287 3961 7.75 6.58

65 0 0

320 1,620

64 3.1 8.6

12,200 11,600

1.4

MISSION II LIGHT

ANTI-ARMOR

9,639 1,684 3216 7.47 6.34

65 0 0

610 1,740

65 2.8 5.7

14,800 8,000

2.1

MISSION III HEAVY

ANTI-ARMOR

9,975 1,684 3432 7.73 6.56

65 0 0

335 1,640

65 3.0 6.1

12,300 3,800

2.0

MISSION IV FERRY

(CLEAN)

9,364 1,684 2875 7.25 6.16

65 0 0

850 1,850

60 2.7 5.4

15.000 10,200

320 130

10.000 10,000

2.6

2.4

FM 101-20

FM 101-20

DIMENSIONS Rotor dia 44 ft Length:

Rotors operating 53 ft. Fuselage 44 ft. 7 in. Span (max lateral) 10 ft. 4 in. Height 12 ft. 1 in. Tread 7 ft. 4 in. Rotor gnd clearance (static) 7 ft. 11 in.

T 9 FT 1 IN

—3 FT U—

JC r

4 FT 11 IN

a

L,

□ 3'

FT I FT 4 IN.

FT N

SC a 10 FT 4 IN

U << a

TO Of. 9*

MAXIMUM LENGTH 53 FT

ROTORS TURNING 11 N

14 FT 8 IN

FT Z oo 6 IN

2 FT 4 IN ‘O r

LL O

i n n 5 FT 2 IN

A û

44 FT 7 IN

ZZP> 7FT u 11 IN

20994 7-9D

Figure 1-5. Principal dimensions AH-IS (ECHS)

1-26 M2 AH-1S(ECAS)J_/ Characteristics


No. and Model (1) T53-L—703 Mfr Lycoming

Engine Spec. No 104.43 Type Free Power Turbine Reduction Gear Ratio 0.3115 Tail Pipe Fixed Area Augmentation None

ENGINE RATINGS

SEA LEVEL STD

Military

Normal

SHIP

1400

1250

RPM MIN

6600 30

6600 Cont.


AIRFRAME: TM55-1520-236-10 & 10CL TM55-1520-236-23 TM55-1520-236-MTF TM55-1520-236-23P TM55-1520-236-PMS

ENGINE: TM55-2840-229-24 TM55-2840-247-23P

Mfr’s Model: Bel 209

The primary mission of this aircraft is anti-armor, providing a stable airborne platform for the tube launched, optically tracked, wire guided missile (TOW) helicopter support. The aircraft is capable of performing this mission from prepared or unprepared areas, under day and night VFR conditions within a temperature range of —25°F to + 125°F.

The gas turbine powered “Cobra TOW” of compact design featuring tandem seating to give both pilot and gunner nearly unlimited visibility. Both crew stations have flight control and fire control systems permitting flexibility in division of functions under all normal and emergency situations.

A mission designed fuselage coupled with the 540 roto system gives a low vibration level plus increased maneuverability and speed. Four wing stores stations and an integral chin turret provide a high degree of armament versatility with the capability of quickly changing a wide combination of weapons to match the desired mission. Reliability and maintainability are ensured through the use of many UH-1 parts which have been combat proven.

The AH-IS (EGAS) has a crashworthy fuel system with closed circuit refueling capability, and a tractor tailrotor system.

DEVELOPMENT

Development contract Production contract .. First Prod. Del

. Jan 1977

.Jun1977 . Sep 1978

FEATURES u Armor protection for crew and


external stores on wings. Stability Control Augmenta-

tion System (SAS) eliminates stabilizer bar and provides a stable gun platform.

Helmet Sight Subsystem TOW Missile Subsystem XM138RMG XM97E1 Turret Subsystem 10 KUA Alternator

PERSONNEL

Anti-Armor Mission Pilot 1

Co-Pilot/Gunner 1

Ferry Mission Pilot Co-Pilot • •

r»Ti~

LOADING


(c) Calculated

LB.

6,580 (C)

9,541 10,000 9,661 9,987

10,000 10,000

(C) (C) (C) <C)

FUEL AND OIL

Fuel: Grade JP^/5 Spec M1L-T-5624 No. tanks 2 Location Fuselage Qty 262 gal.

Oil: Spec MIL-L-7808/

MIL-L-23699 No. tanks I Location Fuselage Qty 3.4 gal.

AVIONICS/ ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS / NSN

NSN 1520-00504-9112 Lin K29694,

COSTS: Refer to Table 4-3, Page 4-5.

NOTES:

JJ AH-IS (EGAS) will be deployed to TO&E units beginning in Jan 79. 2J AH-IS (EGAS) will initially be fielded without the XM138 rocket management subsystem (RMS). Estimate field retrofit to

i during4M^v/Dec 79 time frame. ~ durin^H^^vi

FM

101-20

1-27

1-13. Loading and Performance — Typical Mission AH-1S (EGAS)

CONDITIONS MISSION I

SCOUT

MISSION II LIGHT

ANTI-ARMOR

MISSION III HEAVY

ANTI-ARMOR

MISSION IV FERRY

(CLEAN)

TAKEOFF WEIGHT (lb) Fuel at 6.5 Ibs/gal (Grade JP-4) (lb) Payload (lb) Takeoff Power Loading (lb SHP) Disk Loading (lb sq ft) Autorotation Speed (Min R/D) (kn) Takeoff Ground Run at SL (ft) Takeoff to Clear 50 ft (ft) Vertical Rate of Climb at SL (fpm) Maximum Rate of Climb at SL (fpm) Speed for Max R/C at SL (kn) lîme: SL to 5000 ft (min) Time: SL to 10,000 ft (min) Service Celing (100 fpm) (ft) Absolute Hovering Ceiling (ft)

COMBAT RANGE (nmi) Average Cruise Speed (kn) Cruising Altitude (Initial) (ft) Cruising Altitude (Final) (ft) Total Mission Time (hr)

COMBAT RADIUS (nmi) Average Cruise Speed (kn) Cruising Altitude (Outbound) (Min/Max)..(ft) Cruising Altitude (Inbound) (ft) Total Mission Time (hr)

10,000 1,101 3,461 7.75 6.58

65 0 0

320 1,620

64 3.1 8.6

12,200 11,600

9,661 1,684 3,081

7.47 6.34

65 0 0

610 1,740

65 2.8 5.7

14,800 8,000

9,987 1,532 3,407

7.73 6.56

65 0 0

335 1,640

65 3.0 6.1

12,300 3,800

9,541 1,684 2,961

7.25 6.16

65 0 0

850 1,850

60 2.7 5.4

15.000 10,200

320 130

10.000 10,000

2.6

1.4 2.1 2.0 2.4

FM101-20

1-28

1-14. Loading and Performance — Typical Mission AH1S (MOD) (PROD) and (EGAS)

CONDITIONS MISSION I SCOUT

MISSION II LIGHT

ANTI-ARMOR

MISSION III HEAVY

ANTI-ARMOR

MISSION IV FERRY

(CLEAN)

COMBAT WEIGHT (lb) Combat Altitude (ft) Combat Speed (kn) Combat Climb (fpm) Combat Ceiling (500 ft/min) (ft) Service Ceiling (100 ft/min) (ft) Absolute Hovering Ceiling (ft) Takeoff Ground Run at SL (ft) Takeoff to Clear 50 ft (ft) Maximum Rate of Climb at SL (fpm) Speed for Max R/C at SL (kn) Max Speed at SL (kn) Basic Speed at 5000 ft (kn)

LANDING WEIGHT. Ground Roll at SL... Total from 50 ft

(lb) .(ft) .(ft)

9,500 Sea Level-

Oto 130 1,800

14,800

0 0

1,800 64

140 140

8,513 0 0

9,140 Sea Level

0 to 130 1,800

16,000

0 0

1,800 64

140 140

7,923 0 0

9,400 Sea Level

0 to 130 1,800

14,800

0 0

1,800 64

140 140

8,043 0 0

8,600 10,000

140 2,000

19,000

0 0

2,000 64

140 140

7,864 0 0

c-i vT

* j

FM 101-20

FM 101-20

1-15. Performance Notes, AH-IS(Hueycobra).

LIGHT SCOUT MISSION - Armed Tactical Helicopter — Radius Start engine; warm-up, takeoff, and climb on course at normal power to 6350 feet initial cruise altitude. Maintain 55-feet-per-minute rate of climb at cruise speed to an altitude of 9800 feet. Descend to sea level and fire rockets during a period of ten (10) minutes combat at normal power. Climb on course to 10,000 feet at normal power and return to home base at cruise speed. Range free allowances are two (2) minutes of normal power for warm-up and takeoff, ten (10) minutes of combat time at normal power, plus ten percent of initial fuel for landing and reserve.

HEAVY SCOUT MISSION - Armed Tactical Helicopter - Radius Start engine, warmup, takeoff, and climb on course at normal power to 5350 feet initial cruise altitude. Maintain 41.6 feet-per-minute rate of climb at cruise speed to an altitude of 7250 feet. Descend to sea level and fire rockets during a period of ten (10) minutes combat at normal power. Climb on course to 10,000 feet at normal power and return to home base at cruise speed. Range free allowances are two (2) minutes of normal power for warm-up and takeoff, ten (10) minutes of combat time at normal power, plus ten percent of initial fuel for landing and reserve.

HOG MISSION — Armed Tactical Helicopter — Radius Start engine, warm-up, takeoff, and climb on course at normal power to 5600 feet initial cruise altitude. Maintain 50-feet-per-minute rate of climb at cruise speed to an altitude of 7200 feet. Descend to sea level

and fire rockets during a period of ten (10) minutes combat at normal power. Climb on course to 10,000 feet at normal power and return to home base at cruise speed. Range free allowances are two (2) minutes of normal power for warm-up and takeoff, ten (10) minutes of combat time at normal power, plus ten percent of initial fuel for landing and reserve.

FERRY MISSION — Clean (Without Auxiliary Tanks) — Range Start engine, warm-up, takeoff, and climb on course at normal power to 10,000 feet initial cruise altitude. Fly out at cruise speeds until ninety percent of initial fuel is consumed and land at remote base. Range free allowance include two (2) minutes at normal rated power for warm-up and takeoff, and ten percent of initial fuel for landing and reserve.

GENERAL NOTES: a. Cruise speed as used above denotes airspeed

for long-range operation and is the greater of the two speeds at which ninety-nine percent of the maximum miles per pound of fuel are attainable at the momentary weight and altitude.

b. Data do not include ground effect.

PERFORMANCE BASIS: a. Power required is based upon “Engineering

Phase B Flight-Test Data”.

b. Power available and fuel flow are based on Lycoming Model Specification No. 104.33, and includes particle separators and filters.

NOTE: AH-IQ Deleted Since Conversion to AH-IS Models is Scheduled for Completion by December 1978.

NOTE: Performance Notes Not Available for AH-1S Models.

Source: DRCPM-CO

1-29

\

Figure 1-6. CH-47A, B, C and D (Chinook), typical (minor differences apparent between A, B, C and D models).

/ /

M-

r

1-30

FM 101-20

DIMENSIONS

— 12 FT5 IN.—

v=

1 J 11 FT. 11 IN

Rotor dia 59 Ft. 1-1/4 In. Length:

Rotor operating 97 Ft. 6-1/2 In.

Rotors folded 51 Ft. Fuselage 51 Ft.

Height 18 Ft. 6-1/2 In. Tread 11 Ft. 11 In. Main rotor gnd clearance:

Idling (fwd) 10 Ft. 11 In. (aft) 18 Ft. 6-1/2 In.

Static (fwd) 7 Ft. 8 In. (aft) 17 Ft. 11 In.

2 t

97 FT 6 1/2 IN.

18 FT

6-1/2 IN

• 7FT II IN STATIC

LQ) Û Q Q Q 10 FT 1 IN.

@1 2 DEG

SI FT

7 FT 4-1/2 IN. STATIC

1 18 IN. MIN GND CLEARANCE

• CONTROLS NEUTRAL

Figure 1-7. Principal Dimensions, CH-47A (Chinook)

1-31.

1-32 1-16. CH-47A (Chinook) Characteristics.


No. & model ..(2) T55-L-7B Mfr Lycoming Engine spec No .. T55-L-7/7B 124.20-A T55-L-7C 124.31

ENGINE RATINGS

SHP RPM ALT MIN T55-L-7 Military 2650 15,150 SL 30 Normal 2200 15,000 SL Cont.

T55-L-7B MUitary 2650 15,800 SL 30 Normal 2200 15,000 SL Cont.

T55-L-7C Max 2850 16,000 SL 10 Military 2650 15,750 SL 30 Normal 2400 15,350 SL Cont.


AIRFRAME: TM55-1520-209-10 TM55-1520-209-23 TM55-1520-209-23P TM55-1520-209-PMS DMWR 55-1500-210

ENGINE: TM55-2840-234-24/1 TM55-2840-234-23P DMWR 55-2840-106

Mfr’s Model: Vertol The principal mission of the CH-47A helicopter is the transport of

cargo, troops, and equipment within the combat area. In addition, this helicopter is suitable for special support functions. It is suitable for operations during day, night, visual, and instrument conditions.

The CH-47A helicopter is a twin-turbine-engine, tandem rotary-wing aircraft. It is powered by two Lycoming T55-L-7 shaft turbine engines mounted on the aft fuselage. The engines simultaneously drive two tandem three-bladed rotary wings through a combining transmission, drive shafting, and reduction transmission. The forward transmission is mounted in the pylon above the cockpit. The aft transmission, the combining transmission, and drive shafting are located in the aft pylon section. A gas-turbined auxiliary power unit, used for starting the engines, is mounted in the aft pylon section. Pods on the sides of the fuselage contain fuel tanks. The helicopter is equipped with nonretractable quadricycle landing gear. The aft wheels are full-swivel type. The entrance door is located at the forward right side of the cabin fuselage section. At the rear of the cabin fuselage section is a hydraulically powered loading ramp. A 16,000 pound cargo hook assembly is provided for transporting external loads. Cargo compartment capacity same for all models (1450 cubic ft.)

DEVELOPMENT '

Date of contract 27 June 1960 First flight 6 September 1961 Production status Completed May 1967

CAPACITIES PERSONNEL

Empty (SPEC) . . Design gross wt. . Max alt gross wt .

Max takeoff . . . Max landing . . .

LB L.F. 18,084 28,550 2.67 33.000 2.00 33.000 2.00 33.000 2.00

FUEL AND OIL

Fuel: Grade JP-4 Spec MILT-5624 No. tanks:

Nacelle (2) 621 gal (50 percent self-sealing)

630 gal (non-

573 gal (crash Oil: resistant)

Spec Temps above

25 F MILL-23699 Temps below

25 F MILL7808 No. tanks. ... 2 Location .... Integral with

engine Qty 7 gal

AVIONICS /ARMAMENT

Cargo compartment: Floor Length Width Height . . . Volume

Forward door: Height . . . Width . . .

228-3/4 sq ft 30 ft, 6 in. 7 ft, 6 in. 6 ft, 6 in. 1487 cu ft

5 ft, 6 in. 3 ft

Crew (normal) Troops .... Litters ....

Refer to chapter 2.

FLYAWAY COSTS / NSN

CH-47A, NSN 1520-00633- 6836, Une K30378, COST $990,717

F*—!

Cargo ramp door: Length Width

6 ft, 6 in. 7 ft, 6 in.

FM 101-20

FM 101-20

1-17. Loading and Performance — Typical Mission, CH-47A (Chinook).

CONDITIONS MISSION MISSION MISSION

FERRY

I II III

Gross weight (lb)

Weight empty (lb)

Payload (lb)

Radius of action (nmi) .

Ferry range (nmi) .

Cruise altitude (ft)

Cruise speed (kn)

^Max @ SL military power (kn)

^Max @ SL normal power (kn)

^Max @ 5000 ft, normal power (kn) .

Hover ceihng OGE 950F, military power, std atmosphere (ft)

Hover ceiling IGE military power, std atmosphere . . (ft)

Service, ceiling

Normal power (ft)

Military power 1 eng out (ft)

R/C Max - military power — SL (ft/min)

28,262

17,932

6000

100

SL

130

130

130

114

6000

11.900

11.900

6000

2750

33,000

18,112

13,400

20

SL

110

110

110

94

7900

9200

9200

1400

2160

33,000

17,552

866

6000

110

110

110

94

7900

9200

9200

1400

2166

5-1. All performance based on NASA standard atmosphere unless otherwise noted. ',2. ^Max reflects airspeed limitations specified in TM55-1520-209-10.

- .-S. CH-47A model specifications 114-X-601.

• =3 p — ■ C

1-18. Performance Notes,CH-47A (Chinook).

FORMULA: MISSION I

Deliver 6000-pound internal payload to any point 100 nautical miles and return with 3000-pound internal payload. Cruise at sea level. Land with 10 percent of initial fuel reserve.

FORMULA. MISSION II

Deliver 13,400-pound external payload to any point 20 nautical miles and return. Equivalent flat

plate of external cargo = 26 sq ft. Cruise at sea level. Return with fuel reserve for 10-minute cruise at return gross weight.

FORMULA: MISSION III

Ferry Range of 866 nautical miles. Land with 10 percent of initial fuel reserve. Climb to 6000 feet, 256 nautical miles. Cruise 6000 feet for 610 nautical miles. Total ferry time: 7 hours, 50 minutes.

Source: DRSTS-WC

1-33

FM 101-20

DIMENSIONS

—12 FT 5 IN.*

r

i •h

Rotor día 60 Ft. Length:

Rotors operating 98 Ft. 10-1/2 In.

Rotors folded 50 Ft. 9 In. Fuselage 50 Ft. 9 In.

Height (overall 18 Ft. 11-1/2 In. Tread 11 Ft. 11 In. Rotor ground clearance:

Static fwd 7 Ft. 4-3/4 In. Idling fwd 10 Ft. 11 In.

110 FT 6 IN

E

98 FT 10-1/2 IN

18 FT 11-1/2 IN. I i l

ro) o o o o 10 FT 11 IN.

g & 1°56

50 FT 9 IN.

—18 IN. MIN GND CLEARANCE

1:34 Figure 1-8. Principal Dimensions, CH-47B and C (Chinook)

1-35

1-19. CH-47B (Chinook) Characteristics.

ENGINE MISSION AND DESCRIPTION

No. & Model .... (2) T55-L-7C Mfr Lycoming Engine spec No.

T55-L-7C 124.31 Engine /rotor gear

ratio 65.93:1

ENGINE RATINGS

SHP RPM ALT MIN Maximum 2850 16000 SL 10 MUitary 2650 15750 SL 30 Normal 2400 15350 SL Cont

TECHNICAL PUBLICATION

AIRFRAME: TM55-1520-227-10/1 TM55-1520-227-23 TM55-1520-227-23P TM55-1520-227-PMS DMWR 55-1500-210

Mfr’s Model: Vertol The principal mission of the CH47B helicopter is to provide air

transportation for troops and cargo. The aircraft can also be utilized for rescue of personnel.

The CH-47B is a large tandem rotor helicopter with built-in accomodations for 24 litter patients and 2 attendants or 33 troops and troop commander. The helicopter is equipped with an unobstructed 30-foot long cargo compartment with straight-in rear loading and has a capacity of over 450 cubic feet. Other features include an external cargo hook of 10-ton capacity and a winch system for loading an auxiliary power unit which powers the utility hydraulic system, thus eliminating the requirement for external ground power sources; stability system provided through Vertol SAS; and provisions for utilizing collapsible fuel tanks to increase the fuel capacity by 2000 gallons. The complete helicopter is designed for operations in temperatures ranging from —25° F to +125°F. ; DEVELOPMENT

Date of contract June 1966 First flight October 1966 Production status Completed February 1968

ENGINE: TM55-2840-234-24/1 TM55-2840-234-23P DMWR 55-2840-106


Cargo compartment: Floor .. 228-3/4 sq ft Length 30 ft, 6 in. Width 7 ft, 6 in. Height 6 ft, 6 in. Volume 1487 cu ft Forward door: Height 5 ft, 6 in. Width 3 ft

Cargo ramp door: Height 6 ft, 6 in. Width 7 ft, 6 in.

Crew . Litters

4 24

or Troops 33

WEIGHTS

LB L.F.

Empty *19,153 Basic *19,194 Design 33,000 3.00 Combat *21,734 Max alternate

gross weight ... 40,000 2.54 Normal takeoff .. 33,000 3.00 Alternate takeoff. 40,000 2.54 Max landing 40,000 2.54

*For basic mission.

FUEL AND OIL

Fuel: Grade JP-4 Spec ..; MIL-T-5624 No. tanks:

Fuselage (2) 621 gal 566 gal

(crash resistant) Oil:

Engine contained oil supply Spec

Temps above 25°F MIL-L-23699

Temps below 25°F MIL-L-7808

Qty 7 gal

AVIONICS / ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS / NSN

CH-47B, NSN 1520-00990-2941 LINE K30383, COST $1,063,448

FM

101-20

9Z

‘l

1-20. Loading and Performance — Typical Mission,CH-47B (Chinook)

CONDITIONS

Estimated gross weight Payload guaranteed (outbound) Payload guaranteed (inbound) Payload estimated (outbound) Payload estimated (inbound)

Vmax at SL/STD, military power Max cruise speed at SL/STD,

normal power, Guaranteed Estimated

V-Cruise (best range) at SL/STD V-Cruise (best range) at 5000 F Max rateof-climb at SL/STD military

power Vertical rate-of-climb at SL/STD,

maximum power Service ceiling at normal power Service ceiling, single engine at military

power Guaranteed Estimated

Hover ceiling, OGE at STD temperature maximum power

Hover ceiling, IGE at STD temperature maximum power, 10 ft wheel height .

Radius of action Guaranteed Estimated

Ferry range

• •

(lb) (lb) (lb) Ob) (lb) (kn)

(kn)... (kn)... (kn)... (kn)...

(ft/min)...

(ft/min)... ... (ft)...

. (ft)...

. (ft)...

. (ft)...

. (ft)...

(nmi)... (nmi)... (nmi)...

BASIC MISSION

I

BASIC MISSION

(DESIGN GW) II

PRIMARY MISSION

III

EXTERNAL PAYLOAD MISSION

IV

MAXIMUM FERRY

MISSION V

30,900 6,000 3.000 7.000 3,500

168-2/

166 145 138.

2,440-2/

2,300-2/ 18,000

6,000 6,050

12,850

16,300

100 100

33,000

9,000 4,500

165-2/

150 163 144 134

2,200-2/

1,800-2/ 16,200

3,650

10,650

14,200

100

40,000

15,900 7,935

145 2/

142 134 114

1,520-2/

60 9,550

700-2'

7,400 .

95

40,000

18,800 0 138Í/.2/

132-1/ lOO-â' 100

1,440

60 8,950

700-2'

7,400

20

40,000

1,075

145-2/

142 134 114

1,520

60 9,550

700-2'

7,400

- \

1,090

FM

101-20

1-37

1-20. Loading and Performance — Typical Mission, CH-47B (Chinook) (CONT).

NOTES:

JAVith external payload equivalent to 26 Sq. Ft. drag area.

•transmission limit.

•^Mission cruise speed.

The above table reflects performance capability only. For approved operational limits which consider all pertinent factors, sèeTM 55-1520-209-10.

For Mission 1 the helicopter shall be capable of hovering at 6000 ft. for ten minutes at 95°F, OGE at the gross weight required for the ' accomplishment of Mission I (guaranteed). The Mission I gross weight includes an outbound payload of 6000 lb., return payload of 3000 lb., and fuel for a radius of 100 nmi.

During Mission HI the helicopter shall be capable of hovering out-of-ground effect at sea level standard, maximum power and at a gross weight of 39,500 pounds (guaranteed).

FM

101-2

0

FM 101-20

1-21. Performance Notes, CH-47B (Chinook).

FORMULA: RADIUS MISSIONS I & II

Warm up, take off, climb on course to 5000 feet at normal power, cruise out at long range speeds to remote base, land, and unload cargo. Without refueling, warm up, take off, climb on course to 5000 feet at normal power, and return at long range speeds. Range- free allowances are 2 minutes of normal power for each warmup .and takeoff, plus 10 percent of initial fuel for reserve.

FORMULA: RADIUS MISSION III

Warm up, take off, cruise out at long range speeds at sea level to remote base, land, and unload outbound cargo, load inbound cargo. Without refueling, warm up, take off, return at long range speeds at sea level, land, and unload cargo. Range-free allowances are 2 minutes of normal power for each warmup and takeoff, plus 10 percent of initial fuel for reserve.

FORMULA: RADIUS MISSION IV

Warm up, take off, cruise out at 100 knots at sea level with external cargo to remote base, detach cargo, and land. Without refueling, warm up, take off, and return at long range speeds at sea level. Range-free allowances are 2 minutes of normal power for each warmup and takeoff, plus 10 minutes of cruise fuel for reserve.

FORMULA: RANGE MISSIONS I & II

Warm up, take off, climb on course to 5000 feet at normal power, cruise out at long range speeds until 90 percent of initial fuel is consumed, land, and unload cargo. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 percent of initial fuel for reserve.

FORMULA: RANGE MISSION III

Warm up, take off, cruise out at long range speeds at sea level until 90 percent of initial fuel is consumed, land, and unload cargo. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 percent of initial fuel for reserve.

FORMULA: RANGE MISSION IV

Warm up, take off, cruise out at 100 knots at sea level with external cargo until 10 minutes of cruise fuel remains, detach cargo, and land. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 minutes of cruise fuel for reserve.

FORMULA: RANGE MISSION V

Warm up, take off, climb on course to optimum cruise altitude at cruise speed, cruise out at long range speeds until 90 percent of initial fuel is consumed. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 percent of initial fuel for reserve.

PERFORMANCE REFERENCES

Vertol Report 114-P-J-602. Detail Specifications for the Model CH-47B Helicopter.

Boeing-Vertol Report 114-AD-601. Estimated Performance Capability of CH-47B and CH-47C Heli- copters.

Lycoming Model Specification 124.31, T55-L-7C Shaft Turbine Engine.

Source: DRSTS-WC

1-38

1-39

1-22. CH-47C (Chinook) Characteristics.


No. & model .... (2) T55-L-11A Mfr Lycoming Engine spec No .. 124.38 Engine/Rotor gear

ratio 64.05:1

ENGINE RATINGS

SHP RPM ALT MIN Max .. . 3750 16000 SL 10 Mil.... 3400 16000 SL 30 Nor ... 3000 15400 SL Cont


Airframe: TM55-1520-227-10/2 TM55-1520-227-23 TM55-1520-227-23P TM55-1520-227-PMS DMWR55-1500-210

Engine: TM55-2840-234-24/2 TM55-2840-234-23P DMWR55-2840-118

Mfr’s Model: Vertol

The principal mission of the CH47C is to provide air transportation for troops and cargo. The aircraft can also be utilized for rescue of personnel.

The CH47C is a large tandem rotor helicopter with built-in accommodations for 24 litter patients and 2 attendants or 33 troops and troop commander. The helicopter is equipped with an unobstructed 30-foot long cargo compartment with straight-in rear loading and has a capacity of over 1450 cubic feet. Other features include an external cargo hook of 10-ton capacity and a winch system for loading an auxiliary power unit which powers the utility hydraulic system, thus eliminating the requirements for external ground power sources; stability system provided through Vertol SAS; and provisions for utilizing collapsible fuel tanks to increase the fuel capacity by 2000 gallons. The complete helicopter is designed for operations in temperatures ranging from —25°F to -f 125°F.

DEVELOPMENT

Date of contract Aircraft in production

CAPACITIES

Cargo compartment: Crew . Floor 228-3/4 sq ft Troops Length 30 ft, 6 in. Width 7 ft, 6 in. Height 6 ft, 6 in. Litters Volume 1487 cu ft Forward door: Height 5 ft, 6 in. Width 3 ft

June 1966 January 1969

PERSONNEL

or

4 33

24

Cargo ramp door: Height 6 ft, 6 in. Width 7 ft, 6 in.

WEIGHTS

LB L.F. Empty M9,723 Basic M 9,772 Design 33,000 3.00 Combat 323,886 Max alternate

gross wt 46,000 2.15 Normal

takeoff 33,000 Alternate

takeoff 46,000 Max landing 46,000 ■^For basic mission.

FUEL AND OIL

Fuel: Grade JP4or JP-5 Spec MIL-T-5624 No. tanks:

Fuselage main.. (2) 621 gal 566 gal (crash resistant)

Fuselage aux... (4) 520 gal 480 gal (crash resistant)

Qty 1141 gal OU:

Engine contained oü supply Spec

Temps above 256 F MIL-L-23699

Temps below 25“ F ..... MIL-L-7808

Qty 7 gal

AVIONICS/ARMAMENT

Refer to chaptër 2.

FLYAWAY COST/NSN

NSN 1520-00871-7308 Lin / K30499 Costs $3,223,625

FM

101-20

1-40

1-23. Loading and Performance — Typical Mission, CH-47C (Chinook).

CONDITIONS

Gross weight

Payload guaranteed (outbound)

Payload guaranteed (inbound)

Payload estimated (outbound) Payload estimated (inbound) Vmax at SL/STD, military power Max cruise speed at SL/STD normal power

Guaranteed Estimated

V-Cruise (best range) at SL/STD V-Cruise (best range) at 5000 ft/STD . . . Rate-of-dimb at SL/STD military

' "pôwèr i v Vèrtical rat’e-bf^climb at SL/STD maximum

power Service Ceiling at normal power Service ceiling, STD temp; single engine . at military power - .

Guaranteed Estimated.

Hover ceiling, OGE at STD temperature, max power

Hover ceiling iGE at STD temperature, maximum power, 10 ft. wheel height . .

Radius of action, Guaranteed Estimated

Ferry range

BASIC MISSION

I

BASIC MISSION

(DESIGN GW) II

PRIMARY

MISSION

III

EXTERNAL PAYLOAD MISSION

IW

MAXIMUM FERRY

MISSION V

. . .(lb)

. . .(lb)

. . .(lb)

. . .(lb)

. . .(lb)

. . (kn)

. . (kn)

. . (kn)

. . (kn)

. . (kn)

(ft/min)

(ft/min)

• • -(ft)

.(ft) • (ft)

•(ft)

.(nmi)

.(nmi)

.(nmi)

39,2002/

12,000 6,000

13,300 6,650

156^

156*/ 141 136

2,045^

1,2202/ 10,200*/

4,000 4,5003' ^

9,600

12,750

100 100

33,000

7,350 3,675

1642/

155 164?/ 140 138

2,8802/

2,5853' 15,0002/

9,5502/

14,750

15,000

100

46,000

19,750 9,875

123*/

123*/ 123*/ 111*/

1,3802/

8,000*/

7,600

100

46,000

23,300 0 lOO^

lOO2' 1002/ 1002/

,1,2602/..

8,000*/

7,600

20

46,000

123*/

123*/ 123*/ 111*/

1,3802/

8,000*/

7,600

1,226

» • •

FM 101-20

i • • 1-23. Loading and Performance — Typical Mission, CH-47C (Chinook) (CONT).

t NOTES:

y With External Payload Equivalent to 26 FT2 Drag Area (Troop Seats Incl.) y Hover Gross Weight at 6000 ft/95°F at 245 RPM. y Transmission Limit. y Structural Envelope. y Mission Cruise Speed (Outbound). y Current Hydraulic System Limit. y At 230 RPM.

2/With 12000 LB Payload.

For Mission I the helicopter shall be capable of hovering at 6000 ft for 10 minutes at 95°F,‘OGE at gross weight required for accomplishment of -Mission I (guaranteed). The Mission I gross weight includes an outbound payload of 12,000 lb., return payload.of 6000 lb., and fuel for a radius of 100 nmi.

(guaranteed). maximum power; andagronweigltt of43,000po«iads v. ' -I'-"V S T/*

x :

■ ' “O ; ,

? 4 • s) ' í'.T'i }-. •

rr"

2 Í

%

FM 101-20

1-24. Performance Notes, CH-47C (Chinook).


Warm up, take off, climb on course to 5000 feet at normal power, cruise out at long range speeds to remote base, land, and unload cargo. Without refueling, warm up, take off, climb on course to 5000 feet at normal power, and return at long range speeds. Range- free allowances are 2 minutes of normal power for each warmup and takeoff, plus 10 percent of initial fuel for reserve.


Warm up, take off, cruise out at long range speeds at sea level to remote base, land, and unload outbound cargo, load inbound cargo. Without refueling, warm up, take off, return at long range speeds at sea level, land and unload cargo. Range-free allowances are 2 minutes of normal power for each warmup and takeoff, plus 10 percent of initial fuel for reserve.

FORMULA: RADIUS MISSION IV

Warm up, take off, cruise out at 100 knots at sea level with external cargo to remote base, detach cargo, and land. Without refueling, warm up, take off, and return at long range speeds at sea level. Range-free allowances are 2 minutes of normal power for each warmup and takeoff, plus 10 minutes of cruise fuel for reserve.

FORMULA: RANGE MISSIONS I & II

Warm up, take off, climb on course to 5000 feet at normal power, cruise out at long range speeds until 90 percent of initial fuel is consumed, land, and

unload cargo. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 percent ^ of initial fuel for reserve.

FORMULA: RANGE MISSION III .

Warm up, take off, cruise out at long range speeds at sea level until 90 percent of initial fuel is consumed, land, and unload cargo. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 percent of initial fuel for reserve.


Warm up, take off, cruise out at 100 knots at sea level with external cargo until 10 minutes of cruise fuel remains, detach cargo, and land. Range-free allowances are 2 minutes of normal power for warmup and takeoff, plus 10 minutes of cruise fuel for reserve.


Warm up, take off, climb on course to optimum cruise altitude at cruise speed, and cruise out at long range speeds until 90 percent of initial fuel is consumed. Range-free allowances are 2 minutes of normal ¿ power for warmup and takeoff, plus 10 percent of I initial fuel for reserve.

PERFORMANCE REFERENCES

Vertol Report 114-PJ-7003, Detail Specification for The CH-47C Helicopter.

Lycoming Report 124.38,T55-L-11 A Engine Speci- fication.

Boeing-Vertol Report 114-AD-601, Estimated Performance Capabilities of CH-47B and CH-47C Heli- copters.

Source: DRSTS-WC

* 1-42

(

Á

FM 101-20

DIMENSIONS

-12 FT 5 IN.*

f

■h HlO FT 6 IN


Rotors operating '99 Ft. 0 In.

Rotors folded . .■ 51 Ft. 0 In. Fuselage 51 Ft. 0 In.

Height (overaU)..... 18 Ft. 7-13/16 In. Tread 11 Ft. 11 In. Rotor ground clearance:

Static fwd 7 Ft. 10-5/8 In. Idling fwd 11 Ft. 7/8 In.

JA E

«P

99 FT

18 FT 7-13/16 IN.

i

LQ) Q Q Q Q 11 Ft 7/8 IN.

2°9

51 FTO IN.

—19.2 IN.MIN GND CLEARANCE

r \

Figure 1-9. Principal Dimensions, YCH-47D (Chinook) 1-43

¿» 1-25. YCH-47D (Chinook) Characteristics.


No. and Model (2)T55-L-712 Mfg Lycoming Engine Spec. No 124.53 Type Turboshaft Reduction Great Ratio 66.96 Tail Pipe Augmentation

ENGINE RATINGS

SHP

SEA LEVEL STD Emergency 4500 Maximum 3750 Interme- diate Maximum Continuous 3000

RPM

16000 16000

MIN 30 10

The essential characteristic for the YCH-47D is a minimum lift 15,000 lbs external cargo at 4000’, 95°, HOGE with a 200-500 fpm VïtOC and a 30 NM radius.

The CH-47 is a medium lift tandem rotor helicopter powered by 2 turbo shaft engines. The helicopter has a 30 ft long cargo compartment with straight-in rear loading with accomodations for 24 litters and 2 attendants or 33 combat equipped troops and troop commander. The helicopter is designed for operations in temperatures ranging from -25® to +125°. The YCH-47D has 3 hooks for transportation of loads externally. The center hook has a capacity of 28,000 lb and the forward and aft hooks each have a 20,000 lb capacity. External loads can be handled separately or rigged for multipoint hook up to improve load stability and increase allowable cruise speed.

DEVELOPMENT

3400 16000 30

16000 -

Date of Contact —

First acft delivered.

, 4 Jun 76

TECHNICAL PUBLICATIONS FEATURES

Airframe:

TM55-1520-240-10 and 10CL TM55-1520-240-23 TM55-1520-240-23P TM55-1520-240-MTF TM55-1520-240-PM

Engine:

TM55-2840-234-24/1 TM55-2840-234-23P DMWR55-2840-118

Cargo Compartment: Length 30 ft 2 in Width 7 ft 6 in Height 6 ft 6 in

Forward Door: Height 5 ft 6 in Width 3 ft 0 in

Cargo Ramp Door: Height 6 ft 6 in Width 7 ft 7 in

APU: Solar T-62T-2B

Operations: Day, night, VMC, IMC

PERSONNEL

Crew 3 Litters 24 (Plus 2 attendants)

or Troops 33 (Plus troop commander)

LOADING LB. Empty 22784 Basic — Design 33000 Combat

Clean — Light Scout — Heavy Scout — Hog

Max. Takeoff 50000 Max. Landing 50000

(C) Calculated • For Basic Mission

FUEL AND OIL

Fuel: Grade JP-4 Spec MIL-T-5624 No. tanks 6 Location Fuselage Qty 1042 Gal

Oil: (Engine) Spec ... MIL-L-23699/7808 No. tanks 1/Eng Location Internal Qty 3.75 Galea

AVIONICS/ARMAMENT

Refer to Chapter 2.

FLYAWAY COST/NSN

LIN Z334 90

FM 101-20

1-45

1-26. Loading and Performance — Typical Missions YCH-47D (Chinook)

CONDITIONS

MISSION 11/

(ROC) MISSION

112/

MISSION 1113/

MISSION IVi/

FERRY MISSION

V5/ DES GW 33000 LB)

Estimated Mission Maximum gross weight (GW) (lb.) Payload guaranteed (outbound) (lb). Payload guaranteed (inbound) (lb). Payload estimated (outbound) (lb). Payload estimated (inbound) (lb). V max at SL/STD, Intermediate power (kn). Max cruise speed at SL/STD, Maximum continous power,

Guaranteed (I™)- Estimated (I™)-

Ave V-Cruise (outbound) O®)- Ave V-Cruise (inbound) (kn)- Max rate-of-climb at Mission Max GW (Intermediate power).... (ft/min). Vertical rate-of-climb at Mission Max GW,

Take off horsepower (ft/min). Service ceiling at maximum continuous power (ft). Service ceiling, single engine at emergency power

Guaranteed (ft). Estimated (ft).

Hover ceiling, OGE at STD temperature Take off horsepower (ft).

Hover ceiling, IGE at STD temperature Take off horsepower. 10 ft wheel height (ft).

Radius of action Guaranteed (nmi). Estimates (mm).

Ferry range (nmi).

425Ó0 15000

T5775

50000

22981

43550 13000

14322 7161

42050

15288

50000

111 142 755

200

129 135

1430

740

130 143 830

0

105 142 715

200

136

1580

825

30 30 30 100 30

167

155 162

3750 (SL)

4200 (SL)

15000 10000 14050

15000

15000

1070

FM

10

1-2

0

FM 101-20

1-26. Loading and Performance — Typical Missions, YCH-47D (Chinook) Cont’d.

NOTES: 1/ Ambient Conditions: 4000 ft/95°F. External load provides a drag area of 50 sq ft and download of 0.8% GW. This is the Required Operational Capability (ROC) Mission.

21 Ambient conditions: SL/STD. External load provides a drag area of 50 sq ft and download of 0.8% GW.

2! Ambient conditions: 4000 ft/95°F.

4/ Ambient conditions: 4000 ft/95°F. External load provides a drag area of 75 sq ft and download of 1.87% GW.

5/ Ambient conditions: Standard atmosphere. Additional ferry fuel is carried in 5 internally mounted auxiliary 600 gal tanks.

Reference: Boeing Vertol Report 145-PJ-7103 Revision D, Detail Specification for Model YCH-47D Helicopter.

\

1-46

FM 101-20

1-27. Performance Notes, YCH-47D (Chinook)

Formula: Radius Mission I, II and IV Warm up, tâke-off, hover, acquire external load, climb vertically at maximum power and cruise outbound at long range speed to drop zone. Hover at drop zone to unload cargo and cruise inbound at long range speed. Range free allowances are 2 minutes of maximum continuous power for warm up and take-off, 2 minutes total hover-out-of-ground-effect, 1 minute vertical climb (200 fpm) and 30 minutes reserve at long range cruise speed. This is the Required Operational Capability (ROC) mission profile.

Formula: Radius Mission III Load cargo internally, warm up, take-off, hover-out-of-ground-effect and cruise outbound to landing zone at long range speed. Land and exchange cargo (inbound load equals Vt outbound load), warm up, take-off, hover- out-of ground effect and cruise inbound at long range speed. Range free allowances are 2 minutes of maximum continuous power for each warm up, take-off and hover plus 30 minutes reserve at long range cruise speed.

Formula: Ferry Mission V Warm up and take-off at sea level and cruise climb to 8000 ft. Cruise at 8000 ft at long range speed to landing zone. Range free allowances are warm up and take-off, 2 minutes at maximum continuous power and a reserve of 10% of initial fuel.

Source: DRCPM-CH47M-T

FM 101-20

Figure 1-10. CH-54A and B (Tarhe), typictd (minor differences apparent between A and B models)

1-48

FM 101-20

DIMENSIONS

®H@) 25 FT 5 IN.

^ flL -19 FT 9 IN.-

Main rotor dia 72 Ft. Length (rotors

operating) 88 Ft. 5 In. Length (fuselage) 70 Ft. 3 In. Height (static) 25 Ft. 5 In. Width (cockpit) 7 Ft. 1 In. Tread 19 Ft. 9 In. Gnd clearance:

Main rotor (idling) 16 Ft. 8 In. Tail rotor 9’ 4"

FT 10U IN.

88 FT 6 IN

72 FT

O

16 FT 8 IN.

(IDLING) 6 FT

V 9 FT 4 IN.

i

70 FT 3 IN.

Figure 1-11. Principal Dimensions, CH-54A (Tarhe)

1-49

1-50

1-28. CH-54A (Tarhe) Characteristics.


No. & model.... (2) T73-P-1 Mfr Pratt & Whitney Spec 2453 Type Axial Weight 9251b

ENGINE RATINGS

T73-P-1 S HP RPM MIN

Military .. .4500 9000 30

Normal rated 4000 9000 Cont.


Airframe: TM55-1520-217-10/1 TM55-1520-217-23-1 TM55-1520-217-23P TM55-1520-217-PMS

Engine: TM55-284Ö-23Ö-23 TM55-2840-230-23P DMWR55-2840-230

Auxiliary Power Unit: TM55-2835-203-24 TM55-2835-203-23P

DM WR55-2835-100

Six-blade main rotor. Rear facing seat for aft pilot/hoist operator

A four-point 20,000 lb capacity load suspension system and a 20,000 lb capacity single point cargo hoist.

Four-blade, anti-torque tail rotor.

Crew (normal) 3 Pilot 1 Copilot 1 Aft pilot 1 Observers 2

Passengers (with Pod Attached) Troops 45

or Litters 24 and Attendants 3

Mtr s Model: Sikorsky S-64E Missions that may be accomplished with the CH-54A helicopter

include: movement of heavy outsized loads, towing of surface vehicles, recovery of downed aircraft, and by use of detachable pods, transportation of personnel, vehicles, and equipment (including Paratroop Operations). Since cargo is carried externally by a hoist, the ground crew may load or unload cargo while the helicopter hovers overhead, thereby extending the operational capability into areas unsuitable for landing. Flattopped fuselage serves as a work platform for servicing engines, rotor systems, and main components.

This helicopter is of the all-metal, single main rotor type with one anti-torque tail rotor. The two gas turbine engines are located above the fuselage. The wheel-type alighting gear consists of two fixed main gear assemblies and a fixed nose gear assembly. The enclosed cockpit forming the nose of the helicopter carries basic accommodations for pilot, copilot, and an aft facing pilot. Conventional helicopter flight controls are provided for forward facing pilot seats. Automatic stabilization equipment is also provided. The aft facing pilot seat has cyclic and directional trim controls and a conventional collective pitch stick. Cargo handling provisions include a hydraulic powered hoist. Space and structural provisions are also made for a cargo sling or towing assembly. *

DEVELOPMENT

First production acft delivered Nov 66

Production status out of production

FEATURES PERSONNEL

Empty Basic Gross

(design) ...

(alternate)..

LB 19,219 21,361

38.000 42.000

L.F.

2.50 2.26

FUEL AND OIL

Fuel: Grade jP-4 0r -5 Spec MIL-T-5624

Qty 1342 (8723 lb. JP-4)

Oil: Spec MIL-L-23699 Q‘y 1.73 gal

AVIONICS/ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS/NSN

CH-54A, NSN 1520-00964-9601 Line K30515, Cost $2,660,828

FM 101-20

FM101-20

1-29. Loading and Performance — Typical Mission, CH-54A (Tarhe)

CONDITIONS 20 MILE RADIUS MISSION

I

FULL FUEL RADIUS MISSION

II

FERRY MISSION

TAKEOFF WEIGHT 4/ (lb) . Fuel ! (lb) . Payload (outbound) 3/ : (lb) . Payload (inbound) : ; (lb) . Takeoff power loading (Ib/bhp ) .. Disd. Loading (Ib/sq ft).. Max rate of climb at SL J/ (fpm)... Max rate of climb (one engine out) 1/ (fpm)... Service ceiling (100 fpm) 2/ (ft)... Service ceiling (one engine out) J/ (ft)...

RANGE (nmi)... Average cruising speed (kn)... Mission time (hrs)...

RADIUS ; ; (nmi)... Average cruising speed (kn)... Mission time I : (hrs)...

LANDING WEIGHT .: (lb)...

42,000 2,790

17,849 19,289

6.36 10.31 1,350

450 8,000 2,000

20 98 0.5

21,615

42,000 8,723

11,916 5,958

6.36 10.31 1,350

450 8,000 2,000

110 100 2.0

22,233

30,084 8,723

4.59 7.44

2,625 1,525

12,000 239 110 2.4

22,233

1/ Maximum power. 2/ Normal power. . ... 3/ Carried by single point hoist or four point load suspension system.* 4/ Includes crew of 3 at 200 lb each. Does not include baggage. Engine Air Particle Separators (EAPS) at 360 lbs or Passive Defense

(Armor). Protection at .1185 lbs. 1 ^

Performance Basis: . . Data Source: Army CH-54A Model Spec No. SER64509-2. , TM 55-1520-217-10/1 Operator's Manual (CH-54A)

Performance is based on powers shown in paragraph 1-21.

FORMULA: MISSION I (20 mile radius, single point load)

Warm up for 2 minutes, takeoff at sea level, standard day conditions and climb at BROC. Cruise out 20 nautical miles at 2000 ft pressure altitude, standard day conditions, to a sea level standard day remote site. Hover for 5 minutes out of ground effect while delivering and picking up cargo. Climb at BROC and cruise back at 2000 ft pressure altitude, standard day conditions, to a sea level standard day home-base. Hover for 1 minute out of ground effect and deposit cargo. Land with 10% initial fuel reserve.

FORMULA: MISSION II (full fuel radius, four point load) ’ ’ ' ' - - ' c* ' ' "i ■ .,

Warm up for 2 minutes, takeoff at sea level, standard day conditions with full.fuel,load. Cruise out as far as possible to a sea level, standard day remote site. Land, idle for 5 minutes, deliver 8t pickup cargó.Takeoff, cruise back to sea level standard day home base. Deposit cargo;-Land with 10% initial fuel reserve. Return load equals one half outbound load.

FORMULA: MISSION III (Ferry)

Warm up 1 minute, takeoff at sea level standard day conditions and cruise out at. best range speed until only reserve fuel remains. Land with 10% initial fuel reserve. • ■ '

Source: DRSTS-WC

1-51

's- ■

3y;

»FT 10 IN.

□

î3d •*9 FT 7 INh^ -1*Ft»IN.~

DIMENSIONS

Main rotor dia 72 Ft. 3 In. Length:

Rotors operating 88 Ft. 6 In.

Fuselage 70 Ft. 3 In.| Height (static) 25 Ft. 4 In. Width (cockpit) 7 Ft. 1 In. Tread 21 Ft. 10 In. Gnd clearance:

Main rotor (idling) 15 Ft. 8 In. Tail rotor 9 Ft. 4 In.

vjK-Vli 3 FT 10-1/2 IN

13 FT««**.

«•FT 8 IN < .

“/a FT 2 IN

5 FT 3 IN STATIC N y

CLCANANCEAT QNÓ8S WEIGHT •FT)m. - *- - ■

^0

2 FT «IN.

25 FT 4 IN.

RETRACTED

9 FT 4 IN. ' 6FT6IN. /9,

I EXTENDED j 9FT4[N-

112. IMaMpal Dimensions. CH-54B (Tarhe)

1-52

<

1-30. CH-54B (Tarhe) Characteristics.


No. & model (2)T73-P-700 Mfr Pratt & Whitney Spec 2456 Type Axial Weight 935 lbs

ENGINE RATINGS

Military Normal

rated

SHP 4800

RPM 9000

MIN 30

4430 9000 J Corit.


Airframe: . TM55-1520-2Í7-Í0/2 TM55-1520-217-23/2 ' TM55-1520-2Í7-23P TM-1520-217-PMS >.

Engine: TM55-2840-230-23 : : " TM55-2840-230-23ÍP DMWR55-2840-23Ö ::

Auxiliary Power Uhit: TM55-2835-203:24 TM55-2835-2Ö3-23P DMWR55-2835:100 !i •

i ■■ ^ A

Mfr’s Model: Sikorsky S-64F

Missions that may be accomplished with the CH-54B helicopter include: movement of heavy outside loads, towing of surface vehicles, recovery of downed aircraft, and by use of detachable pods, transportation of personnel, vehicles, and equipment (including paratroop operations). Since cargo is carried externally by a hoist, the ground crew may load or unload cargo while the helicopter hovers overhead, thereby extending operational capability into areas unsuitable for landing. The’flat top of the fuselage serves as a work platform for maintenance and servicing of the engines, rotor systems and other components of the power train system.

« The CH-54B is an all-metal single, main rotor type helicopter with one anti- torijue tail rotor. It is powered by two gas.turbine engines located above the fuselage. The wheel ;type landing gear consists of two fixed main gear assemblies aqd single fixed, fully swiveling nose gear assembly. The fuselage and landing gear are constructed and assembled in a crane configuration. The enclosed cockpit forming the nose of the aircraft has basic accommodations for pilot, copilot, aft-facing pilot and two observers. Conventional helicopter flight controls

;are provided for the pilot and co-pilot! The ajÇt-.facing pilot has electrically operated cyclic and directional trim controls and a conventional collective pitch control.-An automàtic flight control system (AFÇS) is also provided. Cargo handling capabilities consist of a removable single point hydraulic powered four point load suspension system. Provisions áre also made for installation of a towing kit.; • '"

LB L.F. Empty 19,864 Basic 22,386 Gross (Design).. 47,000 2.0

FUEL AND OIL (USABLE)

Fuel: Grade JP-4 or -5 Spec MIL-T-5624 - Qty :i'342

(8723 lb. JP-4)

Oil: "!r ■; Spec . . MÏL-L-23699 Qty...... 1.73 gal

AVIONICS/ARMAMENT

DEVELOPMENT Refer to chapter 2.

■'“First flight June 1969 •.First production aircraft delivered Dec 1969 ^Production status Out of production

; FEATURES ' PERSONNEL

Six-blade main rotor. Aft-facing pilot/hoist operator. 25.000 lb. capacity four point

. load suspension system. 25.000 lb. capacity single

^ point hoist. Four-blade anti-torque tail rotor.

Grew (normal) 3 Pilot 1 Co-pilot 1 Aft-pilot 1

Observers 2 Passengers (with pod attached)

Troops 45 Litters 24 Attendants 3

FLYAWAY COSTS/NSN

CH-54B, NSN 1520-00113- 5776 Line K30515, Cost $2,817,371

ûi

EM

101-20

FM 101-20

1-31. Loading and Performance — Typical Mission, CH-54B (Tarhe)

20 MILE

RADIUS MISSION

FULL FUEL RADIUS

MISSION

II

FERRY

MISSION

III

TAKEOFF WEIGHT 5/ (lb) .. Fuel (lb).. Payload (outbound)_3/ (lb).. Payload (inbound) 3/ (lb) .. Takeoff power loading (Ib/bhp) .. Disc Loading (Ib/sq ft) .. Max rate of climb at SL 1/ (fpm) .. Max rate of climb (one engine out) 1/ (fpm) .. Service ceiling (100 fpm) (ft) .. Service ceiling (one eninge out) 1/ (ft)

RANGE 4/ (nmi) .. Average cruising speed (kn) .. Mission time (hrs)

RADIUS 4/ (nmi) .. Average cruising speed (kn).. Mission time (hrs)

LANDING WEIGHT (lb)..

47.000

2,906 21,708 23,220

5.95 11.50 1,350

490 10.000 2,000

20 103 0.5

22,650

47.000 8,723

15,891 7,946

5.95 11.50 1,350

490 10.000 2,000

101 100 2.0

21,514

31,109 8,723

3.79 7.36

2,915 1,890

12,000 226 100 2.3

23,258

iy 21 3/ 4/ 5/

Maximum power.

Normal power. Carried by single point hoist or four point load suspension system.

Detailed descriptions of missions are given in paragraph 1-22. Includes crew of 3 at 200 lb each. Does not include baggage. Engine Air Particle Separators (EAPS) at 360 lbs or Passive De-

fense (Armor) Protection at 1285 lbs.

Performance Basis: Data Source: Army CH-54B Model Spec No. SER64279.

TM 55-1520-217-10/2 Operator's Manual (CH-54B)

Performance is based on powers shown in paragraph 1-23.

•*

Source: DRSTS-WC

1-54

FM 101-20

Figure 1-13. ÇH-54A and B (Tarhe), Typical, with Universal Military Pod

£

8>

0 O

(&

U o

r

(S

DIMENSIONS

Length 28 Ft. 1 In. Width 9 Ft. 6 In. Height (Wheels up) ..., 7 Ft. 8 In. Weight:

Empty 3020 pounds Max Load 20,000 pounds

Figure 1-14. Universal Military Pod

1-55

FM 1101-20

1-32. Universal Military Pod CH-54Â and B (Tarhe),

The universal military pod is a semimonocoque structure with a rear loading split door-ramp extending the full width and height of the pod. The split-door construction permits both sides to be opened independently, and reduces the proba- bility of jamming. This arrangement permits easier exit in case of an emergency. Two forward doors, one on each side of the pod, are jettisonable and can be opened from both inside and outside. Each door has a secure locking device to prevent inadvertent opening in flight. Four windows, two on each side, are installed using a rubber push-out type seal and can be removed from both the inside and outside of the pod. A nonstructural panel with a push-out type window is in the forward bulk-head. The window is removable from inside the pod. Additional design features follow:

a- Floor loading is 334 pounds per square foot at any location. In the vehicular tread area the maximum allowable floor loading is 1500 Ibs/sq. ft. The floor is reinforced to accommodate equipment as heavy as a 155 Howitzer. Cargo fittings are flush with the floor and have a load capacity of 5000 pounds each. The spacing of the fittings is a standard 20-inch grid pattern.

b. Pod is attached to helicopter load leveler system. Two rubber strips are attached to the top of the pod, running full width, to prevent chafing between the top of the pod and the bottom of the helicopter. When the pod carries troops (passengers) or litter patients, safety provisions require the insertion of screw actuated pins in the primary adapter fittings. This will prevent jettisoning of the load. The primary missions for the pod are to carry a maximum of 45 troops (passengers) or 24 litter patients and to transport general cargo such as missiles, vehicles, weapons, and general supplies.

c. Pod has a conventional four wheel system with pneumatic tires and may be towed at speeds up to 5 miles per hour on level ground at the maximum gross weight of 20,000 pounds. Each of the four wheels has an independent retraction and extension system manually-operated by the mechanical jacks or alternate hydraulic pumps attached to each wheel gear. These permit the pod to be raised or lowered when fully loaded. This action aids unloading the pod by allowing the use of a fork lift and other cargo moving equipment. To obtain the maximum pod wheel ground clear-

ance of 18 inches, when the pod is attached to the helicopter, full retraction of the pod wheels is possible. Detachment from the helicopter without using winches is made by extending the wheel mechanism.

d. Electrical power is supplied to pod by the ^ helicopter’s electrical system. When the pod is attached to the helicopter, two cables on the front exterior bulk-head of the pod are attached to the ac and dc recentacles on the left side external skin of the helicopter, marked POD PWR AC, DC, ICS. When the pod is not attached to the helicopter, electrical power is supplied from a ground source through cables to the ac and dc receptacles marked EXT POWER 115 VOLTS AC and EXT POWER 28 VOLTS DC 4-9, on the left side of the pod.

e. Lighting for the interior of the pod consists of twelve light assemblies, arranged in parallel lines of six lights each on the ceiling. The forward two lights near the entrance doors are white or red controlled by a switch marked ENTRANCE LIGHTS WHITE AND RED. The eight interior lights are controlled by a switch marked INTER- IOR LIGHTS, ON-OFF. Both switches are on the master switfch panel on the left forward wall of, the pod. The last two lights at the ramp end or the pod are controlled by a switch at the rear on the left wall (figure 4-11) marked CARGO LOAD- ING LIGHTS, ON-OFF. Communication between the pod and the helicopter is through a third cable, in the same area as the electrical power cables. The cable is attached to the ICS outlet on the helicopter and is routed to the interphone control panel for the pod, which is on the forward ceiling. Also in this area is a stowage rack for the 30-foot cable.

f. Electrically-operated ventilating blower with a capacity of 500 cfm is installed on the forward bulk head of the pod and is controlled by a switch marked VENT BLOWER, ON-OFF on the master switch panel. Two exhaust openings are on the right and left sides of the pod in the rear area.

Source: DRSTS-WC

1-56

FM 101-20

. : «y y !

mm m

Figure 1-15. OH-6A (Cayuse)

1-57

FM 101-20

HH 11 8 FT 6 IN

cfnfl 8FT 1 1/2IN-

4 FT 6 13/16 IN.-

-6 FT 9 1/4 IN.

DIMENSIONS

Rotor dia 26 Ft. 4 In. Length:

Rotor operating 30 Ft. 3-3/4 In.

Rotor folded 22 Ft. 9-1/2 In. Height 8 Ft. 6 In. Tread 6 Ft. 9-1/4 In.

5rr L J /C

L 4 FT 3 IN.h DIÄMETER LL

-26 FT 4 IN. DIAMETER

30 FT 3 3/34 IN

Q

1-58 Figure 1-16. Principal Dimensions, OH-6A (Cayuse)

1-33. 0H-6A(Cayuse) Characteristics.

ENGINE No. & model .. (1) T63-A-5A/700 Mfr Detroit Diesel -

Allison Div of GMC

Engine spec No. T63-A-5A 58ÖJ, dtd

30 Sept 1970 T63-A-700 803F, dtd

30 Sept 1970 Amend 1.

ENGINE RATINGS

Output Ratings SHP

Takeoff &mU *317 Normal **270

Output speed SFC lb/

MISSION AND DESCRIPTION

Mfr’s Model: Hughes 500

The principal missions of the OH-6A light observation helicopter are visual observation and target acquisition, reconnaissance, and command control. This helicopter is employed in support of combat companies, and will operate for extended periods of time with only such support as provided by one mechanic with handtools. Normal operation is limited to day or night visual flight conditions.

The light observation helicopter is a single-lifting, 4-blade rotor, 4-place helicopter with a normal gross weight of 2400 lb or less. It is powered by a T63-A-5A/700 free turbine engine with 317 SHP, derated to 252.5 SHP. It incorporates dual flight controls with the secondary cyclic control element easily removable. The flight instruments are limited to those required for day and night marginal visual conditions. The cargo area contains troop-type seats which are easily stowable when not in use.

DEVELOPMENT

SHP- rpm HR

Takeoff & mil .... 6000 0.697 Normal 6000 0.706

Above ratings developed on standard sea level static conditions. •Derated to 252.5 for 5 min

••Derated to 214.5


Airframe: TM55-1520-214-10 TM55-1520-214-23 TM55-1520-214-23P TM55-1520-214-PMS DMWR55-1520-214

Design competition initiated October 1960 Flight evaluation completed June 1964 Production contract May 1965 First production acft deliveries September 1966

FEATURES PERSONNEL

Dual controls. Stowable troop seats.

Crew (normal) Observer Copilot

1 2 1

WEIGHTS

Empty Useful load Pilot Observers (2),

Copilot (1) Cargo Fuel Gross (FAA certified) Max structure

.1158

.1242

. 200

. 600

. 42

. 400

.2400

.2700

FUEL AND OIL

Fuel: Grade JP-4 Spec MILT-5624 Alternate ... JP-5, M1L-T-5624 Qty 61.3 gal(non-crash

resistant) 54.4 gal (crash resistant)

OU: Spec MIL-L23699 Alternate ... MIL-L-7808 No. tanks .. 1 Location ... Engine section Qty 3 qt

Main Transmission: Spec ...... MILL-23699 Alternate ... MIL-L-7808 Qty 8.0 pt

Tail Rotor Transmission: Spec MIL-L23699 Alternate ... MIL-L-7808 Qty 0.5 pt

AVIONICS/ARMAMENT

Refer to chapter 2.

Engine: TM55-2840-231-24 TM55-2840-231-23P

FLYAWAY COSTS/NSN

NSN 1520-00918-1523 Lin K30645 Costs $125,821

U1 <0

FM 101-20

1-60

1-34. Loading and Performance — Typical Mission, OH-6A(Cayuse).

BASIC MISSION

I

ALTERNATE 1A (CLEAN)

II

ALTERNATE 1A (ARMED)

III

FERRY RANGE

IV

HIGH SPEED SEA LEVEL MISSION

V

TAKEOFF WEIGHT Fuel Payload (not including pilot) .... Takeoff power loading Disk loading Speed for Min. R/D Max rate of climb at sea level i/ ... Speed for max R/C, sea level ß.... Time: Sea level to 5000 ft -1/ Time: Sea level to 10,000 ft JA ... Service ceiling (100 fpm)-^ Absolute hover ceiling J/ COMBAT RANGE

Average cruising speed Jlßl ■ ■ ■ ■ Cruising altitude Total mission time

COMBAT RADIUS Average cruising speed3/3/ ■ ■ ■ Cruising altitude Mission time

COMBAT WEIGHT ^ COMBAT ALTITUDE

Combat speed-2/ Combat climb ^ Service ceiling-2/. Absolute hover ceiling J/ Max rate of climb @ sea level ^ . Speed for max R/C, sea level .. Maximum speed Basic speed at 5000 ft -2/

LIMIT FUGHT LOAD FACTORS Maneuver Positive Maneuver Negative

iirrfi./ffrp in

... (lb)

... (lb)

... (lb) (lb/bhp)

(Ib/sq ft) (knots)

.. (fpm) (knots)

(minutes) (minutes) ... (ft). ... (ft). .. (nmi).

(knots). ... (ft). ... (hr). .. (nmi).

(knots) . ... (ft). ... (hr). ... (lb). ... (ft).

(knots) . .. (fpm). ... (ft). ... (ft). .. (fpm).

(knots). (knots). (knots).

(g). (g).

2159 400 400 8.55 3.96 54.0 1925 56.0

2.5 5.3

18.400 11,200

370 104

12,200 3.6 185 104

12,200 3.6

1961 12,200

116 1860

20,950 14.400

2250 55

104 117

2.82 0.50

2400 400 637 4/

9.50 4.41 54.0 1560 58.0 3.3 7.0

15.850 6,500

330 102

9600 3.3 165 102

9600 3.3

2207 9600

112 1680

17.850 10,500

1860 56

102 113

2.54 0.50

2400^/ 400 400 9.50 4.41 54.0 1560 58.0 3.3 7.0

15.850 6,500

316 100

9500 3.2 158 100

9500 3.2

2208 9500

112 1680

17.850 10, 500

1860 56 100 110

2.54 0.50

5/ 2159 400 400

8.55 3.96 54.0 1925 56.0

2.5 5.3

18,400 11,200

294 130 SL 2.3 147 130 SL 2.3

1977 SL

130 2220

20,750 14,100

2220 55

130

2.82 0.50

J/f akeoff power up to 5 minutes. ÎAlô'nualmôwër. ' ' | J^For RADIÜS mission. ^ ' includes copilot at 200 lbs.

6.

FM

101-2

0

f 1-J4ôading and Performance — Typical Mission, OH-6A (Cayuse) (CONT).

iS^Tarte?:7' - *■

“^/inchides-M^27TOT~M-27E-l_Armainent Kit. — T- r-

3JLimiteïby Vne. ' ™ J/At combat altitude and combat weight.

Performance Basis:

a. Army flight test YOH-6A.

b. All performance is out of ground effect and for standard atmospheric conditions. Speeds given are true airspeed.

Oî)

o

i

FM 101-20

1-35. Performance Notes, OH-6A(Cayuse).

FORMULA. RADIUS MISSION I, II, & III

Warm up, take off, climb on course at military power to altitude for best range at average cruise weight. Cruise to remote base at speed for best range. Do not land. Return to home base. Range-free allowances are 2 minutes of normal power for warmup and 10 percent of initial fuel for reserves.

FORMULA: RANGE MISSION I, II, & III

Warm up, take off, and climb on course at military power to altitude for best range at average cruise weight. Cruise to remote base at speed for best range. Range-free allowances are 2 minutes of normal power for warmup and 10 percent of initial fuel for reserve.

FORMULA: RADIUS MISSION V *9 Warm up, take off, and accelerate to maximum

speed. Cruise at sea level at maximum speed, as limited by normal power or Vne to remote base. Do not land. Return to home base. Range-free allowances are 2 minutes of normal power for warmup and lO^percent of initial fuel for reserve.


w Warm up, take off, and accelerate, to^maximum

speed. Cruise at sea level at maximum speed,^limited by normal rated power Vne to remote base. Range-free allowances are 2 minutes of normal power for warmup and 10 percent of initial fuel for reserve.

• •!

GENERAL DATA

FORMULA. FERRY RANGE MISSION IV

Warm up, take off, and climb on course at military power to 5,000 feet. At steady cruise, climb to stay at optimum altitude as weight decreases. Range- free allowance is 2 minutes of normal power for warmup. No reserve fuel allowance.

For detailed planning refer to applicable technical manual.

PERFORMANCE REFERENCE

Hughes Tool Company-Standard Aircraft Char- acteristics (OH-6A).

rv

Source: DRSTS-WO

1-62

FM 101-20

sa

on

.98

OÍ 1

! 'iSdc

Figure 1-17. OH-58A and Cf Light observation helicopter (Kiowa), typical

1-63

FM 101-20

5 FT 10 IN

I*— 6 FT 5.4 IN—'

DIMENSIONS

Rotor dia Length:

Rotors operating ..

Blades removed ...

Height: To top of

rotor fairing Tread of skids .. Main rotor:

Disk area Blade area....

Tail rotor: Disk area Blade area ....

. 35;Ft. 4 In.

40 Ft.111.8 In.

32 Ft. 2.0 In.

.. I’Ft1; 7.o’ln.

..,6 Ft. 5.4 In.

£ . .. 979.8 Sq. Ft. . 38.26Sq. Ft..

i

, .20.97 Sq. Ft. ... 2.26 Sq. Ft. h"

i

BLADE DROOP

STA 107.1 2° 7

20 FT0.5 IN

I 9 FT 7. 0 IN 5 FT 4.7 IN

STATIC 1 FT 8.0 IN ODD

CG> ©/) UNITED STATES ARMT

STA // 107.5 STATIC

6 FT 8.0 IN 5 FT 2.0 IN

8 FT 1.3 IN 32 FT 2.0 IN

TURNING) 2 FT 3^^ ¡

HT ;; 1.5.JN J

'6 FT=5.7 IN

TUNNING 7 FT 08 IN

40 FT 11.8 IN

12 FT 7.1 IN

1 FT 1.0 IN

¿gr /o

6 FT 5.20 IN 4.0' SB FT

5a ► .

1-64 Figure 1-18. Principal Dimensions, OH-58A (Kiowa

1-65

1 -36. OH-58A (Kiowa) Characteristics.

ENGINE I

No. & model .. Mfr Engine spec. no.

Type

Length Width Height Weight Helicopter rotor

gear ratio ....

(1) T<53-A-700 Allison Corp. 803-F Amend-

ment 1 Axial-centrifugal

compressor, free turbine

41 in. 15.5 in. 18 in. 135 lbs.

17.44:1

ENGINE RATINGS

Standard Sea Level Static Conditions

SHP RPM DUR Takeoff 317 6000 5 min. Normal 270 6000 Cont.* ♦Derated for Transmission


AIRFRAME: TM55-1520-228-10 TM-55-1520-228-23 TM55-1520-228-23P TM55-1520-228-PMS DMWR 55-1520-228

ENGINE; TM55-2840-231-24 TM55-2840-231-23P DMWR 55-1520-231 DMWR 55-1520-109


„ Mfg’s Model: Bell 206A f i M

The missions for which the OH-58 A Helicopter are employed are: visual observation, target acquisition, reconnaissance, and command control. The helicopter is readily adaptable to utility tasks at the combat company level without use of special kits or special attachments. The helicopter is organic to division, brigade, battalion, or equivalent level, and capable of continuous daily operation in the forward area, with maximum availability to the tactical commander. Normal operation is limited to day and night visual and marginal visual flight conditions.

The OH-58A can perform an unarmed observation mission with a 260-mile range or 3.0-hour endurance at a takeoff gross weight of 2760 pounds. It can perform a scout mission, armed with the M-27E-1 weapon system and 2000 rounds of ammumtion, with a range at 230 miles at a takeoff gross weight of 2967 pounds.

This helicopter is the single engine, single main rotor type. The fuselage is divided into three main sections; the forward section which

provides the cabin and fuel cell enclosures as well as the pylon support, the intermediate section which supports the engine provides the equipment and electronics compartments, and the tail boom which supports the horizontal stabilizer, the vertical stabilizer, and the tail rotor. The free turbine engine is mounted aft of the main rotor horizontally on top of the fuselage. The landing gear is the shock-absorbing skid type.

DEVELOPMENT

First production aircraft delivered May 1969 Last production aircraft November 1973

FEATURES PERSONNEL

Dual controls Rear seat palletized Cargo platform Two bladed seesaw

Crew (normal) Observer .... Copilot

rotor system

1 2 1

; WEIGHTS

LOADING LB - LF. • t - n ’ * • • • IT

Empty 1671.1 Empty (with armor) 1813. Basic 1766.2 3.50 Design 3000 2.50 Combat

Unarmed mission .... 2842.7 2.64

Armed mission . 3000 2.50 Max structural . . 3000 2.50

tv s

FUEL AND OIL

Fuel: Grade JP-4 Spec MIL-T-5624 Alternate .. .JP-5, MIL-T-5624 Emergency .. MIL-G-5572

w/o TCP No. Tanks ... 1 Location .... Fuselage Qty ... 73.0 gal (non-crash resistant)

71.5 gal (crash resistant) Oil: Engine Spec MIL-L-23699 Alternate ... MIL-L-7808 No. Tanks .. 1 Location ... Fuselage

Transmission: Spec MIDD23699 Alternate ... MIL-L-7808

M/RHub ...GradeSO Spec MIL-L-2104

AVIONICS / ARMAMENT

Refer to chapter 2.

FLYAWAY NSN1520-00169-7137, LINE,' K31042, COST, $144,722.

\

FM 101-20

FM 101-20

1 -37. Loading and Performance — Typical Mission, OH-58A (Kiowa). Ù tOjpH

CONDITIONS

1

BASIC MISSION

(Unarmed Observation)

dJ^naJ II'oioH

ALTEREE

(Armed Sêôpt)

296?^/T

lOT

428 bfc.. iT 298I nifi/i

9.84f!!H 3-03,T ;icT

49iei(I bfilH

1600 50

4.0 8.5

17.200 5,400

230 120

10,000 2.47 121 102

12.200 2.47

2770 10,000

99 1120

19,500 8000 1600

50 120-

114 nsr

TAKEOFF WEIGHT Fuel Payload Takeoff Power Leading Disk Loading Speed for Min. R/D Vertical Rate of Climb @ Sea Level Max Rate of climb @ Sea Level ^.

Speed for Max R/C @ Sea Level ... . Time Sea Level to 5000 ft. -1/ Time Sea Level to 10,000 ft. i/ Service Ceiling (100 fpm) 2/ Absolute Hover Ceiling iS

COMBAT RANGE Average speed ... Cruising Altitude Total Mission Time

COMBAT RADIUS Average Speed Cruising Altitude Total Mission Time

COMBAT WEIGHT 3/ Combat Altitude Combat Speed Combat Climb -1/ Service Ceiling3^ Absolute Hover Ceiling

Max R/C @ Sea Level 3/ Speed for Max R/C Max Speed @ Sea Level Basic Speed @ 5000 ft.

2760 455, 170

9.15 2.82

49

1780 48

3.5 7.5

19.000 8,000

260 . 102

14.000 . 2.98

147 102

14.000 2.98 2550

14.000 87

1090 21.000 10,600

1750 48

120 114

J/Takeoff power up to 5 minutes. - - -2/Normal Power. -2/ For Radius Mission. -4/lncludes M-27E-1 Armament Kit. ■ ■

Performance Basis: Bell flight test 206A MOD. All performance is out of ground effect and for standard atmospheric conditions.

ii 1 -38. Performance Notes, OH-58A (Kiowa).

RADIUS MISSION - I & II

RANGE MISSION - I & II

Warmup - Two minutes at normal power at sea level Takeoff and Climb — On course at military power to altitude for best range at average cruise weight Cruise - At speed for best range Reserve - 10% takeoff fuel

Soiirce:DRSTS-WO

1-66 .

FM 101-20

DIMENSIONS

_ Rotor dia 35 Ft. 4 In. Length:

Rotors -.-ôperating 40 Ft. 11.8 In.

Blades . removed 32 Ft. 2.0 In.

• Height: Tatop of

rotor fairing 9 Ft. 7 In. Tread of skids 8 Ft. 5.4 In. Main rotor:

Disk area 979.8 Sq. Ft. Blade area 38.26 Sq. Ft.

Tail rotor: Disk area 20.97 Sq. Ft. Blade area 2.26 Sq. Ft.

o

I—6 FT 5.4 IN.—I

(

32 FT 2 IN.-

-35 FT 4 IN

/TT-I

ss 6 FT 5.2 IN.

EBd ^7 FT 11IN.-

-40 FT 11.8 IN.-

12 FT 9 FT4 N. 9 FT 4.5 IN.

9 FT 6 IN FT IN

□ □. 1 FT4.4 IN t 1 FT1 IN.

6 FT 8 IN. I 6.8 IN.—I

i

8 FT 1.5 IN.

-6 FT

—10 FT 9 IN.

.nM

Figure 1-19 Principal Dimensions, OH-58C (Kiowa) Standard Skid Gear

1-67

FM 101-20

DIMENSIONS

Rotor dia 35 Ft. 4 In. Length:

Rotors operating 40 Ft. 11.8 In.

Blades removed 32 Ft. 2.0 In.

Height: To top of

rotor fairing 9 Ft. 7.0 In. Tread of skids 8 Ft. 5.4 In. Main rotor:

Disk area 979.8 Sq. Ft. Blade area 38.26 Sq. Ft.

Tail rotor: Disk area 20.97 Sq. Ft. Blade area 2.26 Sq. Ft. 7 FT 3 IN

u l?

£

\r>—8 FT.10 IN.

12 FT 6 IN. aro«

FT 9 IN. 10 10 FT

7 FT 2 IN.

3 FT 4.4 IN 2 FT 3 IN

5 FT 9.4 IN E-'

10 FT 6.3 IN.

10 FT 1.5 IN.

1-68 Figure 1-20. Principal Dimensions, OH-58C (Kiowa) High Skid Gear

1-69

wa) Characteristics.

POWER PLANT MISSION AND DESCRIPTION WEIGHTS

No. & model T63-A-720 ; Mfr Detroit_piesei

Allison r-'j Engine spec.no 876 '

Type Axial-centrifugal compressor, free turbine

Length 41.1 Width 19.0 Height 23.2 Weight 158 Helicopter rotor gear ratio 17.44:1

ENGINE RATINGS

Standard Sea Level Static Conditions SHP RPM DUR

Takeoff 317 6000 5 min. Normal 270 600 Cont.* ♦Derated for Transmission


AIRFRAME: TM55-1520-235-10 TM55-1520-228-23 TM55-1520-228-23P DMWR 55-1520-228

ENGINE: TM55-2840-241-23 TM55-2840-241-23P DMWR 55-2840-242

Mfg’s Model: Bell 206.5

The missions for which the OH-58C Helicopter are employed are: Reconnaissance, security, aerial observation and target acquisition functions during daylight hours (stabilized optics), and will provide a limited night time capability (night vision goggles) for the conduct of these tasks. In performing these roles, the Interim Scout Helicopter will operate in cavalry, attack helicopter, and field artillery units.”

The OH-58C can perform an unarmed observation mission with a 185-nm or 2.5-hour endurance at a takeoff gross weight of 3200 pounds.

This helicopter is the single engine, single main rotor type. The fuselage1 is divided into three main sections; the forward section which provides the cabin and fuel cell enclosures as well as the pylon support, the intermediate section which supports the engine provides the equipment and electronics compartments, and the tail boom which supports the horizontal stabilizer, the vertical stabilizer, and the tail rotor. The free turbine engine is mounted aft of the main rotor horizontally on top of the fuselage. The landing gear is the shock-absorbing skid type.

DEVELOPMENT

First production aircraft delivered Anticipated Sept. 78 Last production aircraft

FEATURES

Dual controls Rear seat palletized Cargo platform Two bladed seesaw

rotor system

PERSONNEL .

Crew (normal).

Copilot

LOADING LB Empty 1868.5 Empty

(with armor)... 1976.5 Basic 2337.6 Design 3200 Combat

Unarmed mission 2915.6

Max structural .. 3200

L.F.

FUEL AND OIL

Fuel: Grade JP-4 Spec MIL-T-4624 Alternate . JP-5, MIL-T-5624 Emergency MIL-G-5572 w/o TCP

No. Tanks .. 1 Location ... Fuselage Qty

73.0 gal (non-crash resistant) 71.5 gal (crash resistant)

Oil: Engine Spec MIL-L-23699 Alternate . MIL-L-7808 No. Tanks. 1 Location .. Fuselage

Transmission: Spec MIL-L-23699 Alternate . MIL-L-7808

M/R Hub... Grade 30 Spec MIL-L-2104

AVIONICS / ARMAMENT

Refer to chapter 2.

FLYAWAY

NSN, 1502-01020-4216, LIN *233527, COST $201,898

FM101-20

FM 101-20

1 -40. Loading and Performance — Typical Mission, OH-58C (Kiowa).

CONDITIONS

I

BASIC MISSION

II

ALTERNATE

TAKEOFF WEIGHT Fuel Payload Takeoff Power Loading Disk Loading Speed for Min. R/D Vertical Rate of Climb @ Seal Level Max Rate of Climb 1/

(Unarmed Observation) (Armed Scout)

2915.6 456 284

N/A

2.98 50

6300

Service Ceiling Absolute Hover Ceiling

COMBAT RANGE _!/ Average Speed Cruising Altitude

16,400 12,300

185 NM 100 K

Total Mission Time COMBAT RADIUS

Average Speed Cruising Altitude Total Mission Time....

COMBAT WEIGHT.... Combat Altitude Combat Speed Combat Climb Service Ceiling Absolute Hover Ceiling

Max R/C @ Sea Level.... Speed for Max R/C Max Speed @ Sea Level.. Basic Speed @ 5000 ft....

120 K

-1/ 2000 ft. @ 95°F

NOTE: Final performance data not available pending completion of testing.

1-41. Performance Notes,OH-58C (Kiowa).

RADIUS MISSION - I & II

RANGE MISSION - I & II

Warmup — Two minutes at normal power at se level Takeoff and Climb — On course at military power to altitude for best range at average cruise weight Cruise — At speed for best range Reserve — 10% takeoff fuel

Source: DRSTS-WO

1-70

FM 101-20

iii

Figure 1-21.TH-55A (Osage)

1-71

7 F

T 5

-1/2

IN

.

FM 101-20

ä

8 FT 2-1/2 IN.

.6 FT 6-1/2 IN. -LANDING GEAR

FULLY COMPRESSED

DIMENSIONS .

Rotor dia f.J. '!...22 Ft. 4 In Length:

Rotors . , n operating 28 Ft. 3 In static 22 Ft. 4 In

Fuselage 21 Ft. 10-3/4 In. Span (max

lateral) Height :. 8 Ft. 2-1/2 In. Tread . .6 Ft. 3 In, Ground clearance

Static 3 Ft. 2-1/2 In

1 4 FT 3 IN.

3^;

Ï — 3 FT 4 IN

27 FT9-1/2 IN.

28 FT 3 IN.

10 IN. 12 FT 6 IN.

7 FT 2 IN

S

6 FT 7-1/2 IN. :■

22 FT 4 IN.

Figure 1-22. Principal Dimensions, TH-55A (Osage)

5 i 1

1-72

1-73

1-42 TH-55A (Osage) Characteristics.


No. & model .. (1) HI0-360-B1 Al Mfr Lycoming Engine spec. No. 2313-b Engine to main

rotor rear ratio 6:1

ENGINE RATINGS

BHP RPM MIN Takeoff 180 2900 5 Normal 160 2700-2900 Cont.

max power


AIRFRAME: TM55-1520-233-10

COMMERCIAL MANUALS (Contractor Supported)

ENGINE: COMMERCIAL MANUAL

The TH-55A helicopter is manufactured by the Hughes Heli- copter Company, Culver City, California. The mission of the TH-55 A is the training of military pilots in the basic operation and performance of a helicopter. Training will be accomplished only in CONUS and from an established aviation training base.

The two-place cabin is designed to accommodate an instructor and student with the seating arrangement side by side. The instructor and student each have a complete set of flight controls.

DEVELOPMENT

Contract awarded June 1964 First acft delivered November 1964 Last production acft April 1969

FEATURES

Dual Controls

PERSONNEL

Crew (Normal) 2 Instructor Pilot 1 Student Pilot 1

LB T

Empty 1Ó08.Í Useful load. 591.9 Design (gross) .... 1600 Combat NA Max takeoff 1600

FUEL AND OIL

Fuel: Grade 115/145 Spec ’MIL-G-5572 No. of tanks 1

Location Left rear of cabin

Qty 25 gal Oil:

Spec Temps above +60° F MIL-L-22851 Type II

Temps below +60°F MIL-L-22851 Type III

No. tanks 1 Qty 2 gal

AVIONICS / ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS / NSN

N SN-1520-00758-0289, Line K31153, COST $35,590

FM 101-20

FM 101-20

1-43. Loading and Performance — Typical Mission, TH-55A (Osage).

CONDITIONS

Fuel at 6.0 Ib/gal (grade 115/145)

Payload

Cruise speed at SL

Rate of climb at SL

Endurance (2700 rpm)

(lb),

(lb) .

(kn)

(ft/min)

Hover ceiling, out of ground effect, 110°F

Normal autorotation speed

Normal autorotation rotor speed

Autorotation rate of descent at 1000 ft, 100oF, 480 rpm and 45 knots

Altitude necessary to regain normal autorotation rotor speed from lower red line

Range (normal)

Service ceiling

(ft)

(kn)

(rpm)

(ft/min)

(ft)

(nmi)

. (ft). .

BASIC MISSION

150

591.9

75

1400

2-1/2 hrs at 65 knots cruise speed (min)

1000 (min)

45

480

1900 (max)

200 (max)

200

11,000

Source: DRSTS-WO

# 1-74

FM 101-20

:<ov¿

n:i n i fr

HfiSaH

m

Figure 1-23. UH-1B (Iroquois)

« 1-75

FM 101-20

DIMENSIONS

■9 FT3-I/2IN.

4

P

H 34 IN


Rotors : operating '53 Ft.

Rotors static 53 Ft. Fuselage 42 Ft] 8-1/2 In. Span (max

lateral) 9-Ft. 3-1/2 In. Height 14 Ft. 8-1/2 In. Tread 8 ft. 4-3/4 In. Rotor gnd clearance:

(static) 7 Fti 4-3/4 In.

<4

52 FT 10-3/4 IN

m

/ .= 13 FT 2-1/2 IN.

A LZ

38 FT 5 IN I I

42 FT 8-1/2 IN

Figure 1-24. Principal Dimensions, UH-1B (Iroquois) r

1-76

¿¿■I

1-44. UH-1B (Iroquois)Chafácteristics:

ENGINE i MISSION AND DESCRIPTION WEIGHTS A-'

No. & Model—.-(il) T-SS-L-.l 1¡C/ v

-1 ID Mfr Lycoming Type Free power

turbine Red. gear ratio . 0.3119 Tailpipe Fixed area Augmentation . None

ENGINE RATINGS

T53-L 11C/D

Rating/SL SHP SFC Output RPM

Max (takeoff) 1100 0.682 6610

Mil 1000 0.690 6610 NRP 900 0.702 6610


AIRFRAME: TM55-1520-219-10 TM55-1520-219-20&34 TM55-1520-210-23P TM55-1520-219-PMS TM66-1600-219-MTF

ENGINE: TM65-2840-229-24 TM&6-M40-229-23P DMWR &6-2840-113

^ ¡ Mfr’s Model: Bell 204 ?

The principal missions of the UH-1B are the transport of personnel, special teams or crews, equipment, supplies, and to serve as an aerial weapons platform. Universal pylons are attachable to the aircraft to serve as mounts for weapons or external fuel tanks. It may also be used for medical evacuation and as an instrument trainer. These missions may be performed from prepared or unprepared takeoff and landing areas, under instrument operations including light icing, and day or night flight.

The gas-turbine-powered UH-1B is of compact design having a low silhouette. The two-bladed main rotor and the two-bladed tail rotor are of all-metal construction. The fuselage is of semimonocoque construction

Sliding cabin doors allow straight-through loading. Litters may be loaded from either side or both sides simultaneously. The cargo floor is knee-high to facilitate loading. The copilot’s controls are removable, thus providing accomodations for a passenger in the copilot’s seat or, when the copilot’s seat is removed, additional cargo area. Some UH-lB’s, have complete provisions for a variable speed, power-driven hoist supported by a swing boom, capable of lifting personnel or up to 600 pounds of cargo.

DEVELOPMENT

Date of contract First flight First delivery . ..

December 1960 March 1960 December 1961

CAPACITIES Inside clearance

Cargo area: Length (overall).... 4 ft Width (floor level). . 6 ft, 8-1/2 in. Heiît (max) 4 ft

Copilot area: Length (overaB) ,.. 4 ft, 7 ia. Width (floor iavai).. 2 ft, 7 ». Height (max) 4ft

Mam CMBB door Height (max) 4 ft Width (max 4 ft

Limit floor loads (overall)

Cargo area 300 Ib/sq ft Copilot area 75 Ib/sq ft

Usable cubage Cargo area 140 cu ft Copilot area 20 cu ft

PERSONNEL Basic mission

Crew (pilot and medical attendant)

Litters Traaaport mttsion

Crew Pameapcrs

dlliimtf Crew Patteagera

Trainer Crew (instructor &

student) Ferry

Crew

2 3

1 4

1 7

7: -u - * -HLB

Empty (calculated).... 4557

Basic 4825 Design ......... 6600 Combat *6596 Max takeoff 8500 Max landing 8500 *For basic mission.

:L.F.

3.0 3.0 2.3

FUEL AND OIL

Fuel: Grade JP4/5 Spec . MIL-T-5624 No. tanks:

Fuselage (2) 165 gal Ferry (1) 350 gal

Total qty 515 gal Oil:

Spec MIL-L-7808 or

MIL-L-23699 No. tanks 1 Location Fuselage Qty 3-1/4 gal

AVIONICS / ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS / NSN

cc s

NSN-I62O4X)713-9012, LINE K31749, COST $244,780

FM

101-2

0

1-78

1-45. Loading and Performance — Typical Missions, UH-1B (Iroquois).

CONDITIONS

TAKEOFF WEIGHT

Fuel at 6.5 Ib/gal (grade JP-4) Payload (outbound) Payload (inbound) Takeoff power loading^. Disk loading

Autorotation speed (min R/D) Takeoff ground run at SL1/ Takeoff to clear 50 ft 1/ Vertical rate of climb at SL -1/

Maximum rate of climb at SL 2/... Speed for max R/C at SL Time: SL to 5000 ft 2/ Time: SL to 10,000 ft 2/ Service ceiling (100 fpm)2/. Absolute hovering ceiling 1/.

COMBAT RANGE ii^ Average cruise speed Initial cruising altitude Final cruising altitude

Total mission time COMBAT RADIUS W

Average cruise speed Cruising altitude (outbound)

Cruising altitude (inbound) Total mission time

FIRST LANDING WEIGHT^ Ground roll at SL Total from 50 ft

COMBAT WEIGHT 3/ Combat altitude

-Combat speed .. Combat climb 2/ Combat ceiling (500 ft/min) 12/

.... (lb)

.... (lb)

.... (lb)

.... (lb) .

. (lb/bhp) . (lb/sqft) . ... (kn) . .... (ft) .

.... (ft) .

... (fpm) .

... .(fpm) .

... (kn) .

... (min) .

... (min) .

.... (ft) .

.... (ft) .

... (nmi) .

... (kn) .

.... (ft) .

.... (ft) .

.... (hr) .

.. (nmi) . .. (kn) . ... (ft) . ... (ft) . ... (hr) .

... (lb) .

... (ft) .

... (ft) .

... (lb) .

... (ft) .

. . . (kn) .

.. (fpm)

... (ft)

TRANSPORT

(CARGO OR

PASSENGER)

6762 1073 800

0 7.04 4.45 57.0

0 0

1610 1910 57.0

2.7 6.0

18,000 11,500

230 106

2000-4000 2000-4000

2.25 112.7

106 2000-4000 2000-4000

2.22 6253

0 0

5453 2000-4000 :

.106 2190

22,400

ARMED 12/

7500 1073

0 0

6.86 4.35 56.5

0 0

1780 2010 56.5

2.5 5.4

17,000 12.400

210 90

20004000 20004000

2.45 94.5

90 20004000 20004000

2.4 6145

0 0

7241 20004000

100 1590

15.400

INSTRUMENT TRAINER

6088^ 1073^

0 0

6.34 4.00 55.6

0 0

2330 2300 55.6

2.3 4.9

20,200 14,900

218 106

20004000 20004000

2.12 98.8 106

20004000 20004000

1.95 5631

0 0

5631 20004000 j. 1

106 —

2050 21,400

FERRY

8390 3348 3/

0 0

8.74 5.52 60.1

0 0

1250 60.1 4.6

....1

8800 11/

695 103.4

20004000 20004000

6.88

5377 20004000

—106 2220

22,600

FM

101-2

0

1-79

•)'S ) ifiU!"!' -v.' 0 - ) 'J'J' roil.; ' jCfjii

1-45?s ;L6aarng:andPerformance-typicajMissions,UH-1B(Iroquois)(CONT.)

¡ÏW ■ 'ÓÜ

^wCT^TTT“ -'/Nfï’-.<îr ”r»:H

i í '"Or:

S:>;ü lis—

-.5‘ÇCO

3Î50

CONDITIONS ( TRANSPORT

(CARGO OR PASSENGER)

.rtOr'siioO ARMED 12/

JINSURDMENT TRAINER

soooôuu FERRY

Service ceiljng(100 ft/min)-2/> 12/ , Absolute hovering ceiling-l/> 12/ .

Takeoff ground run at SL-1/

Takeoff to clear 50 ft-1/

Maximum rate of climb at SL-2/..

Speed for max R/C at SL

Max speed at SL-â/

Basic speed at 5000 ft^/

LANDING WEIGHT-^

Ground roll at SL

Total from 50 ft

. (ft)

• (ft)

• (ft)

• (ft) (fpm)

• (kn)

■ (kn)

• (kn) • (lb) . (ft)

• (ft)

23,100 18,200

0

, . 0.

2740

54.2

120

117.5

4996

0

0

16,000 9000

0

0

1740

58.0

105

100

5639

0

0

22,200 16,800

0 ' - o

2620

54.6

120 117.5

5188

0

0

23,250 18,500

0

0

2810

54.1

120

117.5

5377

0

0

-i^Takeoff power.

■2/NormaI rated power. 2/For RADIUS mission if radius is shown.

^Vne limit.

2/ Includes crew of 2 at 400 lb.

& Includes crew of 1 at 200 lb. 2/ Includes 1 x 350 gallon tank.

& Based on engine specification takeoff shaft horsepower available.

^ Three 250-lb litter patients. !iy Detailed descriptions of RADIUS and RANGE missions are given in paragraph 1-33.

Ü/ Above service ceiling. L2/ Armed W/M-21 subsystem.

Performance Basis:

a. Power required based on FTC-TDR-62-21, “YUH-1B Category II Performance Tests.”

b. Power available and fuel flow are based on Lycoming Model Specification No. 104. 16-B.

c. All data are at 6600 engine rpm.

d. Except for Ferry Mission, data do not include ground effect.

FM 101-20

FM 101-20

1-46. Performance Notes, UH-1B (Iroquois).

FORMULA: RADIUS MISSION I

Warm up, take off, climb on course to 2000-4000 feet at normal power, proceed at cruise speeds to remote base, and land. Without refueling, warm up, take off, climb on course to 2000-4000 feet at normal power, and return at cruise speeds. Range-free allowances are 4 minutes of normal power for warmups and takeoffs plus 10 percent of initial fuel for reserve.

FORMULA: RADIUS MISSION II

Warm up, take off, climb on course to 2000-4000 feet at normal power, proceed at cruise speeds to remote base, and land. Without refueling, warm up, take off, climb on course to 2000-4000 feet at normal power, and return at cruise speeds. Range-free allowances are 4 minutes of normal power for warmups and takeoffs plus 10 percent of initial fuel for reserve.

FORMULA . RADIUS MISSION III

Warm up, takeoff, climb on course to 2000-4000 feet at normal power, proceed at cruise speeds to remote base, and land. Without refueUng, warm up, take off, climb on course to 2000-4000 feet at normal power, and return at cruise speed. Range-free allowances are 10 minutes of normal power for warmups and takeoffs plus 20 minutes at speeds for maximum endurance at sea level, plus 5 percent of initial fuel for reserve.

FORMULA: RANGE MISSION II

Warm up, take off, climb on course to 2000-4000 feet at normal power, and proceed at cruise speeds until 90 percent of initial fuel is consumed. Range-free allowances are 2 minutes of normal power for warmup and takeoff^plus 10 percent of initial fuel for reserve.


Warm up, take off, climb on course to 2000-4000 feet initial altitude at normal power, proceed at cruise speeds to remote base, and land. Range-free allowances are 5 minutes of normal power for warmup and takeoff, plus 20 minutes at speeds for maximum endurance at sea level, plus 5 percent of initial fuel for reserve. Æ


Warm up, take off, climb on course to 2000-4000 feet initial altitude at normal power, maintain 30 feet per minute rate of climb to final altitude of 2000-4000 feet, and proceed at cruise speeds until 90 percent of initial fuel is consumed. Range-free allowances are 2 minutes of normal power for warmup and takeoff plus 10 percent of initial fuel for reserve.

GENERAL NOTES

a. Cruise speed as used above denotes airspeed for long-operation or maximum permissible speed, whichever is lower.

b. Except for ferry mission takeoff, data do not include ground effect.

Source: DRSTS-WU

1-80

FM101-20

■COMlCH ¡iba-

3S;!- íg'IC

qíiirnKV/ ■.ms

L

‘Ií;J*.VO

1 s-..

■:A.

Figure 1-25 UH-lC and M, (Iroquois), typical

1-81

FM 101-20

DIMENSIONS

7 FT 1 3/4 IN

9 FT 13/32 IN.

[J

Rotor dia 44 Ft Length:

Rotors operating 53 Ft,

Rotors static 53 Ft. Fuselage 42 Ft. 8 In.

Span (max lateral) 9 Ft. 1/2 In.

'Height 14 Ft. 9 In. Tread 8 Ft. 4-1/2 In. Rotor gnd clearance:

(static) 7 Ft. 4-1/2 In.

— 8 FT V/-J IN.—J

44 FT

-52 FT 10% IN

to

t

o-

12 FT 8 IN. FT 9 IN

==3

1-82

Figure 1-26. Principal Dimensions, UH-1C (Iroquois)

1-83

1-47 UH-1C (Iroquois) Characteristics.


No. & model (1)T53-L

-11C/D

Mfr Lycoming Engine spec No ... 104.22-B & .28 Type Free power

turbine Red. gear ratio ... 0.3119 Tailpipe Fixed area Augmentation .... None

ENGINE RATINGS

T53-L-11C/D Output

Rating/SL SHP SFC RPM Max (takeoff) 1100 0.682 6610 MU 1000 0.690 6610 NRP 900 0.702 6610


Mfr’s Model: BeU The principal missions of the UH-1C helicopter are transporting

personnel, special teams or crews, equipment and supplies; medical evacuation; ambulance service; reconnaissance and security; point target and area fire by attachment of appropriate weapons; and instrument trainer. These missions may be performed from prepared or unprepared takeoff and landing areas, under instrument operations including light icing, and day or night flight. Navigation may be by dead reckoning or by use of radio aids.

The main difference between the UH-1C and UH-1B is the main rotor system. The UH-1C has the 540 rotor system which has a flexure plate, hinge-half type hub and a wider chord blade. The 540 rotor system provides a more stable gun platform, higher maximum gross weight, and higher forward speed. Some UH-lC’s have complete provisions for a variable speed, power driven hoist supported by a swing boom, capable of lifting personnel or up to 600 pounds of cargo.

DEVELOPMENT

Contracting agency AVSCOM Delivery schedule June 1965 thru November 1967


ENGINE: TM55-2840-229-23P TM55-2840-229-24 DMWR 55-2840-113

CAPACITIES

Cargo area: Length (overall) .. 4 ft Width (floor

level) 6 ft. 8-1/2 in.

Height (max) ... 4 ft CopUot area:

Length (overaU) .. 4 ft, 7 in. Width (floor

level) 2 ft, 7 in. Height (max) .... 4 ft

Main cargo door Height (max) 4 ft Weight (max) 4 ft

Limit floor loads (overall) Cargo area 3001b/sqft CopUot area 75 Ib/sq ft

Usable cubage Cargo area 140 cu ft CopUot area 20 cu ft

PERSONNEL

Basic mission Crew (pUot and medical

attendant) 2 Litters 3

Transport mission Crew 1 Passengers 4

Alternate Crew 1 Passengers 7


student) 2 Ferry

Crew 1

WEIGHTS

LB L.F. Empty 4830 Gross 9500

FUEL AND OIL

Fuel: Grade JP-4/5 Spec MIL-T-5624 Qty 242 gal

OU: Spec MIL-L-7808

or MIL-L-23699

Qty-Engine .... 4 gal Qty-Transmission

and gear boxes 2.8 gaL

AVIONICS / ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS / NSN

NSN, 1520-00997-8862, Line K31767, Cost, $224,415

FM101-20

FM 101-20

1-48. Performance — Typical Mission, UH-1C (Iroquois).

Takeoff distance (ft) Rate of climb (fpm) Service ceiling (ft) Cruise speedi/ (kn) Max speed (kn) Range ;... (nmi) Landing distance (ft)

0 2,420

21,100 92-110

140 300

0

-i/Normal rated power (6600 rpm) at sea level.

Source: DRSTS-WU

1-84

FM 101-20

DIMENSIONS

7.FT 1 3/4 IN

9 FT 13/32 IN

[•“8 FT 4'/j IN.-*]

Rotor dia .7.V. 44 Ft. Length: •

Rotors ' operating 53 Ft. Rotors static .’53 Ft.

Fuselage i-.... '.. 42 Ft. 8 In. Span (max

lateral) 9 Ft. 1/2 In. Height 14 Ft. 9 In. Tread 8 Ft. 4-1/2 In. Rotor gnd clearance:,

(static) 7 Ft. 4-1/2 In. Ç,

44 FT

52 FT 10% IN.

/

n—n cz-

m 12 FT 8 IN 13 FT9 IN

2:

Figure 1-27. Principal Dimensions, UH-1M (Iroquois)

1-85 /

1-S6

1-49. UH-1M (Iroquois) Characteristics.


No. & model (1) T53-L-13B

Mfr Lycoming Engine spec No .. . 104.22-B & .28 Type Free power

turbine Red. gear ratio ... 0.3119 Tailpipe Fixed area Augmentation .... None

ENGINE RATINGS

T53-L-13B

Ratio Max Mil NRP

ae/SL SHP (Takeoff) 1101

SHP 1100 1000 900

Output SFC RPM

0.682 6610 0.690 6610 0.702 6610




Mfr’s Model: Bell

The principal missions of the LfH-lMhelicopter are transporting personnel, special teams or crews, equipment and supplies; medical evacuation; ambulance service; reconnaissance and security; point target and area fire by attachment of appropriate weapons; and instrument trainer. These missions may be performed from prepared or unprepared takeoff and landing areas, under instrument operations including light icing, and day or night flight. Navigation may be by dead reckoning or by use of radio aids.

The main difference between the UH-lMand UH-1C is the T53-L-13.1. The UH-lMhas the 540 rotor system which has a flexure plate, hinge-half type hub and a wider chord blade. The 540 rotor system provides a more stable gun platform, higher maximum gross weight, and higher forward speed. Some UH-lMs have complete provisions for a variable speed, power driven hoist supported by a swing boom, capable of lifting personnel or up to 600 pounds of cargo.

Empty Gross

LB L.F. 4830 9500

FUEL AND OIL

DEVELOPMENT

Contracting agency AVSCOM Delivery schedule June 1965 thru November 1967

CAPACITIES

Cargo area: Length (overall) Width (floor

level)

4 ft

6 ft. 8-1/2 in.

Height (max) ... 4 ft Copilot area:

Length (overall) . . 4 ft, 7 in. Width (floor

level) 2 ft, 7 in. Height (max) .... 4 ft

Main cargo door Height (max) 4 ft Weight (max) 4 ft

Limit floor loads (overall) Cargo area 300 Ib/sq ft Copilot area 75 Ib/sq ft

Usable cubage Cargo area 140cuft Copilot area 20 cu ft

PERSONNEL

Basic mission Crew (pilot and medical

attendant) Litters

Transport mission Crew Passengers

Alternate Crew Passengers


student) Ferry

Crew

Fuel: Grade JP-4/5 Spec M1L-T-5624 Qty 242 gal

Oil: Spec MIL-L-7808

or MIL-L-23699

Qty-Engine .... 4 gal Qty-Transmission

and gear boxes 2.8 gal

AVIONICS / ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS / NSN

NSN, 1520-00809-2631, Line, K31804, COST $247,758

• • • • • it.. * r

FM

10

1-2

0

FM 101-20

1-50. Performance — Typical Mission, UH-1M (Iroquois).

Takeoff distance . Rate of climb ... Service ceiling ... Cruise speed^/.. . Max speed Range Landing distance

..(ft) (fpm) ..(ft) . (kn) . (kn) (nmi) ..(ft)

0 2,420

21,100 92-110

140 300

0

-iAiormal rated power (6600 rpm) at sea level.

Source: DRSTS-WU

1,87

FM 101-20

a

IM

Figure 1-28 UH-1D, H, V, (Iroquois), typical

1-88

FM 101-20

DIMENSIONS

Rotor día Length:

Rotors operating ...

Rotors static.. Fuselage

Span (max lateral)

Height Tread Gnd clearance

(static, against stops)

48 Ft.

57 Ft. 1 In. 57 Ft. 1 In. 41 Ft. 11-1/4 In.

9 Ft. 4 In. . 14 Ft. 5-1/2 In. .. 8 Ft. 6-1/2 In.

6 Ft. 6 In.

7 FT 8-7/16 IN.

r 9 FT 13/32 IN

-8 Ft 6-39/64 IN

1 FT 9 IN es rm 48 F*

¡7“ 9FT4IN.

2 FT 6-1/2 IN.— —

44 FT 10-3/32 IN

11 FT 8-21/32 IN.

1 8 FT 6 IN.

11 FT 9-3/4 IN

□ □ □ □

1 FT. 3 IN GROUND LINE DESIGN GROSS WEIGHT

40 FT 7-3/32 IN.—

-41 FT 11-5/32 IN

Figure 1-29. Principal Dimensions, UH-1D and H (Iroquois)

1-89

14 F

T 5

-1/2

IN

.

1-90 1 -51. UH-1D (Iroquois) Characteristics.


No. & model .. <1)T53-L-11C/D

Mfr Lycoming Engine spec No 104.28 & ,22-B Type .... Free power

turbine Red. gear ratio . 0.312 Tailpipe' Fixed area Augmentation . None

ENGINE RATINGS

T53-L-11C/D

Ratini "g Mäx(takeoff) 1100 0.682 6610

SHP Output

SFC RPM

Mil NRP

1000 0.690 6610 900 0.702 6610

Mfr’s Model: Bell 20S The missions of the UH-1D include transportation of personnel,

equipment and supplies, medical evacuation, delivery of protective fire by attachment of appropriate weapons, and instrument training. These missions may be performed from prepared or unprepared takeoff and landing areas, under instrument operations including light icing, and day or night flight.

The UH-1D is of compact design having a low silhouette. The semimonocoque fuselage is of all-metal construction as are the tail rotor blades and the two main rotor blades.

The sliding doors along each side of the cabin allow simplified straight-through loading from either side or both sides simultaneously. This capability is especially useful while loading or unloading litter patients. The knee-high cargo floor also contributes to loading ease. Since the copilot’s controls are removable, an extra passenger can be carried. If the copilot’s seat is also removed, an extra 8.75 square feet of cargo area is gained. Some UH-lD’s have complete provisions for a variable speed, power-driven hoist supported by a swing boom, capable of lifting personnel or 600 pounds of cargo while hovering. Retrofit of a crashworthy fuel system with closed circuit refueling capability is being accomplished on the UH-1D aircraft.

TECHNICAL PUBLICATION CAPACITIES

AIRFRAME: TM55-1500-219-MTF TM55-1510-210-10 TM55-151Ö-210-20 TM55-1510-21Ó-34 TM55-1520-220-PMS TM55-1510-210-PM

ENGINE: TM55-2840-229-23

1TM55-2840-229-23P DMWR 55-2840-113

Inside clearance Cargo area:

Length (overall) .. 7 ft, 8 in. Width (floor

level) .8 ft Height (max)- 4 ft, 1 in.

Copilot area: Length (overall) .. 3 ft, 7 in. Width .2 ft, 7 in. Height (max) . .. .4 ft

Main cargo door Height .4 ft Width (max) . ;.. .6 ft, 2-1/2 in Height above ground 2 ft

Limit floor loads Cargo area 300 Ib/sq ft Copilot area 75 Ib/sq ft

Usable cubage Capacity

Cargo area .....'. 220 cu ft Copilot area 20 cu ft

PERSONNEL

Basic mission Crew 1 Passengers 4

Alternate Crew ; 1 Passengers 12

Litter evacuation Crew (pilot & medical

. attendant) 2 . Litters v ........ 6 ;

! Cargo Crew 1

Ferry mission Crew (pilot & copilot) 2

LB L.F. Empty (calculated).. 5098

Design 6600 3.0 Combat 9500 2.2 Max takeoff 9500 2.2 Max landing 9500

FUEL AND OIL

Fuel: Grade JP-4/5 Spec MIL-T-5624 No. tanks:



Spec ...' MIL-L-7808 or

MIL-L-23699 No. tanks 1 Location Fuselage Qty 4-1/2gal

AVIONICS / ARMAMENT

Refer to chapter 2. '

FLYAWAY

NSN 1520-00859-2670, LINE, K31786, COST, $237,504

• •

FM 101-20

1-91

1 -52. Loading and Performance — Typical Missions, UH-1D (Iroquois).

CONDITIONS BASIC

(PERSONNEL CARRIER)

TRANSPORT (CARGO OR

TROOP) LITTER

EVACUATION FERRY

TAKEOFF WEIGHT Fuel at 6.5 Ib/gal (grade JP-4) (lb) Payload (outbound) (lb) Payload (inbound) (lb) Takeoff power loading-^/ (Ib/SHP) Disk loading 0b/«I ft) Autorotation speed (min R/D) (kn) Takeoff ground run at SL (6600 rpnO-1/ (ft) Takeoff to clear 50 ft (6600 rpm)-í/ (ft) Vertical rate of climb at SL (6600 rpm)-i/ (fpm) Maximum rate of climb at SL-2/ (fpm) Speed for max R/C at SL (kn) Time: SL to 5000 ft-2/. (min) Time: SL to 10,000 ft-2/ (min) Service ceiling (100 fpm)-2/ ;... (ft) Absolute hoverineceiling (6600 rpm)-L/ (ft)

COMBAT RANGE ÍW (nmi) Average cruise speed (kn) Cruising altitude (initial) (ft) Cruising altitude (ftnal) (ft) Total mission time (hr)

COMBAT RADIUS Uy (nmi) Average cruise speed (kn) Cruising altitude (outbound) (min/max) (ft) Cruising altitude (inbound) (ft) Total mission time (hr)

FIRST LANDING WEIGHT-2/ (lb) Ground roll at SL (6600 rpm) (ft) Total from 50 ft (6600 rpm) (ft)

COMBAT WEIGHT-2/f (ib) Combat altitude (ft) Combat speed-4/. , (jy,) Combat climb-2/ ... (fpm) Combat ceiling (500 ft/min)^/ (ft) Service ceiling (100. ft/min)-2/ . ; (ft) Absolute hovering ceding (6600 rpm)-!/ (ft) Takeoff ground run at SL (6600 rpm)4/. (ft)

7334-6/ 1359 800

0 6.66 4.05 51.7

0 0

1620 1730 51.7

2.9 6.2

20.900 10,100 305.4

102 20004000 20004000

2.99 149

105.4 20004000 20004000

2.92 6655

0 0

5855 20004000

• 110 2020

25,000 26.900 17,600

0

8954-6/ 1359 2420

0 • 8.14

4.95 55.5

0 0

420 1220 55.5

4.1 9.8

14,900 2300

259 99

20004000 20004000

2.62 134

103.5 20004000 20004000

2.7 8220

0 0

5800 20004000

110 2040

25,200 27,000 17,800

0

6930-6/ 1359

0 1500-2/ 6.30 3.83 50.9

0 0

1960 1880 50.9

2.6 5.6

22,400 12,200

143.3 103.5

20004000 20004000

2.34 6320

0 .0

7800 20004000

118 1520

16,200 18,900

7600 0

8795-6/ 3309-2/

0 0

7.99 4.86 55.1

0 0

580 1260 55.1

4 93

15,200 3000 705.0

103 20004000 20004000

637

5753 20Q04000

110 2070

25,400 27,200 18,100

0

FM 101-20

1-92

1-52. Loading and Performance — Typical Missions, UH-1D (Iroquois) (CONT).

CONDITIONS

BASIC (PERSONNEL

CARRIER)

TRANSPORT (CARGO OR

TROOP)

LITTER EVACUATION FERRY

Takeoff to clear 50 ft (6600 rpm) 1/ (ft) Maximum rate of climb at SL<* (fpm) Speed for max R/C at SL (kn) Max speed at SL ^ (kn) Basic speed at 5000 ft 4^ (kn)

LANDING WEIGHT & (lb) Ground roll at SL (6600 rpm) (ft) Total from 50 ft (6600 rpm) (ft)

0 2360 48.8 120 119

5247 0 0

- 0 2400 48.7 120 119

5247 0 0

0 156Ö 52.8

117.5 118

7143 0 0

0 2420 48.6 120 119

5753 0 0

J/ Takeoff power. 2/ Normal rated power.

3/For RADIUS mission if radius is shown. 4/ Vne limit.

& Includes crew of 2 at 400 lb. è/Includes crew of 1 at 200 lb.

2/ Includes two 150-gallon ferry tanks.

& Based on engine specification takeoff shaft horsepower. Six 250-pound litter patients.

la' Detailed descriptions of RADIUS and RANGE missions are given in paragraph 1-38.

Performance Basis: a. Power required based on Bell Model 204B FAA Flight Test. b. Power available and fuel flow based on Lycoming Model Specification No. 104.28. c. All data are at 6400 rpm unless otherwise noted.

FM

101-2

0

FM 101-20

1-53. Performance Notes, UH-1D (Iroquois).


Warm up, take off, climb on course to 2000-4000 feet initial altitude at normal rated power, proceed at long range cruise speed to remote base, land, and unload passengers. Without refueling, warm up, take off, climb on course to 2000-4000 feet at normal rated power, and return at long range cruise speed. Range-free allowances are 4 minutes at normal rated power for warmups and takeoffs plus 10 percent of initial fuel for reserve.


Warm up, take off, and climb on course to 2000-4000 feet at normal rated power. Cruise climb on course at long range cruise speed to final altitude of 2000-4000 feet. Proceed at long range speed to remote base, land, and unload cargo or troops. Without refueling, warm up, take off, climb on course to 2000-4000 feet at normal rated power, and return at long range cruise speed. Range-free allowances are 4 minutes at normal rated power for warmups and takeoffs plus 10 percent of initial fuel for reserve.

climb on course to 2000-4000 feet at normal rated power, and return at long range cruise speed. Range-free allowances are. 4 minutes at normal rated power for warmups and takeoffs plus 10 percent of initial fuel for reserve.

FORMULA: RANGE MISSION I

Warm up, take off, and climb on course to 2000-4000 feet initial altitude at normal rated power. Proceed at long range cruise speed to remote base and land. Range-free allowances are 2 minutes at normal rated power for warmup and takeoff plus 10 percent of initial fuel for reserve.


Warm up, take off, and climb on course to 2000-4000 feet at normal rated power. Cruise climb on course at long range cruise speed to final altitude of 2000-4000 feet. Proceed at long range cruise speed to remote base and land. Range-free allowances are 2 minutes at normal rated power for warmup and takeoff plus 10 percent of initial fuel for reserve.

FORMULA: RANGEMISSION HI


Warm up, take off, and climb on course to 2000-4000 feet at normal rated power. Proceed at long range cruise speed to remote base, land, and pick up litter patients. Without refueling,. warm up, take off,

Warm up, take off, and climb on course to 2000-4000 feet at normal power. Cruise climb on course at long range cruise speed to final altitude of 2000-4000 feet. Proceed at long range cruise speed to remote base and land. Range-free allowances are 2 minutes at normal rated power for warmup and takeoff plus 10 percent of initial fuel for reserve. " .

Source: DRSTS-WU

1-93

1-94

1-54. UH-1H (Iroquois) Characteristics.

ENGINE

No. & model.... (1)T53-L-13B


Mfr’s Model: BeU 205

Mfr Lycoming Type 104.33 Red. gear ratio .. 0.312 Tailpipe Fixed area Augmentation .. None

ENGINE RATINGS

T53-L-13B Output

Rating/SL SHP SFC RPM Mil 1400* 0.580 6300 NRP 1250* 0.598 6040

* 1400 SHP flat rated to 1100 SHP.

The UH-1H is a modified UH-1D with the T53-L-13 turbine engine. The basic description and mission are the same for both aircraft. The advantages over the UH-1D are takeoff distance, rate of climb, range, endurance, and overall mission capabilities. All future production of the UH-1D will be the UH-1H model. Some UH-lH’s have complete provisions for a variable speed, power-driven hoist supported by a swing boom, capable of lifting personnel or up to 600 pounds of cargo while hovering. Production and retrofit of a crashworthy fuel system with closed circuit refueling capability is being accomplished on the UH-1D/H aircraft.


Inside clearance Basic mission

TECHNICAL PUBLICATION-

0$^

/AIRFRAME: TM55-1520-210-10 TM55-1520-210-23 TM55-1520-210-23P TM55-1520-210-PMS TM55-1500-219-MTF TM55-1500-210-PM

ENGINE: _ TM55-2840-229-23

[55-2840-229-23P DMWR55-2840-113

Wi

Cargo area: Length (overall).. 7 ft, 8 in. Wdth (floor leVel) 8 ft

Height (max) 4 ft, 1 in. Copilojt area:

Length (overall) .. 3 ft, 7 in. Width 2 ft, 7 in. Height (max) .... 4 ft

Main cargo door ight (max) 4 ft idth(max) 6 ft, 2-1/2 in.

Height above ground 2 ft

Limit floor loads Cargo area 300 Ib/sq ft Copilot area 75 Ib/sq ft

Usable cubage Capacity:

Cargo area 220 cu ft Copilot area .... 20 cu ft

Crew Passengers

Alternate

Crew Passengers

Litter evacuation Crew (pilot & medical

attendant) Litters

Crew

Cargo

Ferry mission Crew (pilot & copilot)

1 4

1 12

2 6

1

2

WEIGHTS

Empty

Design Combat ... Max takeoff Max landing

LB L.F.

5132 6600 3.0 9500 2.2 9500 2.2 9500

FUEL AND OIL

Fuel: Grade JP-4/5 Spec MIL-T-5624 No. tanks:



Spec MIL-L-23699 or


AVIONICS / ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS / NSN

NSN 1520-00087-7637, LINE, K31795, COST $618,055

FM

101-20

1-95

1-55. Loading and Performance — Typical Missions, UH-1H (Iroquois).

CONDITIONS ( \

BASIC

(PERSONNEL

CARRIER)

TRANSPORT

(CARGO OR

TROOP)

LITTER

EVACUATION FERRY

TAKEOFF WEIGHT (lb)

Fuel at 6.5 Ib/gal (grade JP-4) (lb)

Payload (outbound) (lb)

Payload (inbound) (lb)

Takeoff power loading^/ (Ib/SHP)

Disk loading (lb/sq ft)

Autorotation speed (min R/D) (kn)

Takeoff ground run at SL (6600 tpm)L/ (ft)

Takeoff to clear 50 ft (6600 rpm)!/. (ft)

Vertical rate of climb at SL (6600 rpm)!/ (fpm)

Maximum rate of climb at SL!/ (fpm)

Speed for max R/C at SL (kn)

Time: SL to 5000 ft 2/. (min)

Time: SL to 10,000 ft 2 (min)

Service ceiling (100 fpm)2/ (ft)

Absolute hovering ceiling (6600 rpm)!/. (ft)

COMBAT RANGE \Q/ (nmi)

Average cruise speed (kn)

Cruising altitude (initial) (ft)

Cruising altitude (final) (ft)

Total mission time (hr)

COMBAT RADIUS L9( (nmi)

Average cruise speed (kn)

7644 6/

1370

800

0

6.94

4.22

61

0

0

1620

1653

61

3.1

6.2

18340

14,800

275

111

2000-4000

2000-4000

2.46

141

111

9264i/

1370

2420

0

8.42

5.11

65

0

0

420

1126

65

4.6

9.9

13,960

4000

250

105

2000-4000

2000-4000

2.37

124

107

7414 i/

1370

0

1500i/

6.74

4.10

60

0

0

1960

1691

60

2.9

5.9

19,140

16,000

9305 i/

33202/

0

0

8.45

5.14

65

0

0

580

1112

65

4.1

10.2

13,640

3600

676

110

20004000

20004000

6.13

133

121

FM 1

01-2

0

1-96

1-55. Loading and Performance — Typical Missions, UH-1H (Iroquois) (CONT).

CONDITIONS

BASIC

(PERSONNEL

CARRIER)

TRANSPORT

(CARGO OR

TROOP)

LITTER

EVACUATION FERRY

Cruising altitude (outbound) (min/max)

Cruising altitude (inbound)

Total mission time

FIRST LANDING WEIGHT.!/

Ground roll at SL (6600 rpm)

Total from 50 ft (6600 rpm)

COMBAT WEIGHT!/

Combat altitude

Combat speed!/

Combat climb!/

Combat ceiling (500 ft/min)!/

Service ceiling (100 ft/min)!/

Absolute hovering ceiling (6600 rpm)!/ ,

Takeoff ground run at SL (6600 rpm)!/

Takeoff to clear 50 ft (6600 rpm)!/. . . .

Maximum rate of climb at Si!/

Speed for max R/C at SL

Max speed at SLl/

Basic speed at 5000 ft!/.

LANDING WEIGHT!/

Ground roll at SL (6600 rpm)

Total from 50 ft (6600 rpm)

. . (ft)

. . (ft)

..(hr)

. . (lb)

. . (ft)

• • (ft)

. . (lb)

. . (ft)

• (kn)

(fpm)

. . (ft)

. . (ft)

• • (ft)

• • (ft)

- ■ (ft)

(fpm)

• (kn)

• (kn)

• (kn)

• ■ Ob)

• - (ft)

• ■ (ft)

2000-4000

2000-4000

2.73

6997

0

0

6197

2000-4000

116

2256

23,550

24,070

21,300

0

0

2232

55.9

120

120

6977

0

0

20004000

20004000

2.54

8584

0

0

6164

20004000

116

2276

23,694

24,210

21,400

0

0

2251

55.8

120

120

8584

0

0

20004000

20004000

2.38

6789

0

0

8289

20004000

120

1370

15,960

16,842

11,600

0

0

1399

62.0

120

120

6789

0

0

6316

20004000

116

2200

23,150

23,680

20,700

0

0

2178

56.1

120

120

6316

0

0

FM

10

1-2

0

• • • 1-55. Loadingand Performance — Typical Missions, UH-1H (Iroquois)(CONI).

-L/ Takeoff power.

%J Normal rated power.

.1/ For RADIUS mission if radius is shown.

4/ Vne limit.

Includes crew of 2 at 400 lb.

4/ Includes crew of 1 at 200 lb.

-2/ Includes two 150-gallon ferry tanks.

-§/ Based on engine specification takeoff shaft horsepower.

-2/ Six 250-pound littér patients.

IS/ Detailed descriptions of RADIUS and RANGE missions are same as shown in paragraph 1-38.

Performance Basis:

a. Reference operator’s Manual Army Model UH-1D H Helicopter TM 55-1520-210-10.

b. AU data are at 6600 rpm unless otherwise noted.

Source: DRSTS-WU

■JJ- .

io

FM 101-20

DIMENSIONS

Rotor dia Length:


Rotors static.. Fuselage

Span (max lateral)

Height Tread Gnd clearance


48 Ft.

.... 57 Ft. 1 In.

.... 57 Ft. 1 In. 41 Ft. 111/4 In.

9 Ft. 4 In. . 14 Ft. 5-1/2 In. .. 8 Ft. 6-1/2 In.

.6 Ft. 6 In

7 FT 8-7/16 IN.

9 FT 13/32 IN.—

- 8 FT 6-39/64 IN. -

D 48 FT

^ 9 FT 4

2 FT 6-1/2 IN.— —

44 FT 10-3/32 IN.

II FT 8-21/32 IN

8 FT 6 IN.

$ 11 FT 9-3/4 IN.

a □□ 1 FT 3 IN. GROUND UNE DESIGN GROSS WEIGHT

40 FT 70/32 IN

41 FT 11-5/32 IN.

Figure 1-30. PrincipEil Dimensions, UH-1V (Iroquois)

1-98

14 F

T 5-1

/2 I

N.

1-99

• • • • 1-56. UH-1V (Iroquois) Characteristics.

ENGINE

No. & model..

Mfr Type Red. gear ratio Tailpipe Augmentation

(1)T53-L-13B

Lycoming ■ 104.33 0,312 ; Fixed area None

ENGINE RATINGS

T53-L-13B

Rating/SL SHP Mil 1400* 0.580 NRP 1250* 0.598

Output SFC RPM

6300 6040



AIRFRAME: TM 1500-219-MTF TM55-1520-210-10 TM55-1520-210-23 & 34 TM55-1520-210-23P TM55-1520-210-PMS TM55-1520-21Ö-PM



Mfr’s Model: Bell 205

The UH-IV is a UH-1H converted to a niedical evacuation aircraft, the only difference in the conversion is installation of.DME.and a radar altemeter. This aircraft will be furnished all fned evàc units.

DEVELOPMENT

First flight (Similar aircraft) First acft delivered Mar 79

CAPACITIES

See Page 1-91.

PERSONNEL

See Page 1-91.

WEIGHTS

LB L.F. Empty

5132 Design 6600 3.0 Combat 9500 2.2 Max takeoff 9500 2.2 Max landing 9500

FUEL AND OIL

Fuel: Grade JP-4/5 Spec !.. MIL-T-5624 No. tanks: y

Fuselage ..:... (2) 209 gal Ferry (1)300 gal


Spec MIL-L-23699 or


AVIONICS / ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS / NSN

NSN, 1520-01043-4949, Line, COST $618,055

FM 101-20

FM 101-?0

DIMENSIONS

Rotor dia Length:


Rotors Static.. Fuselage Span (max

Lateral) Height Tread .. Gnd clearance


48 Ft.

• • • 57 Ft. 1 In. • • • • 57 Ft. 1 In. 41 Ft. 11-1/4 In.

9 Ft. 4 In. • 14 Ft. 5-1/2 In. • ■ 8 Ft. 6-1/2 In.

6 Ft. 6 In.

h 9 FT 13/32 IN

8 FT 6-39/64 IN.

i

-1 FT. 9 IN

D 48 F».

¡0=3—= 9 FT 4 IN r~L_-i£

D

2 FT6-1/2 IN.-

■44 FT 10-3/32 IN.

11 FT 8-21/32 IN.

8FT6IN.

C2 Cl 11 FT 9-3/4 IN.

EEr GROUND LINE DESIGN GROSS WEIGHT 1 FT 3 IN.

40 FT 7-3/32 IN

41 FT 11-5/32 IN.

1-100 Figure 1-31. Principal Dimensions EH-1H (Quick fix)

■10

FT

. 2-

1/2

IN.

• • • • • 1-57. EH-1H (Quick Fix) Characteristics


No. & model.. ..

Mfr Type Red. gear ratio .. Tailpipe Augmentation . .

(1)T53-L- 13B

Lycoming 104.33 0.312, , Fixed area None

ENGINE RATINGS

T53-L-13B

The EH-1H is a modified UH-1H configured to carry ECM equipment in the passenger/cargo area. The basic dynamic components and airframe are the same as the standard aircraft.

The mission for the EH-1H weapon system consists of airborne search, collection and jamming countermeasures of enemy single channel radio communications. This information is provided to Division/Brigade commanders in tactical situations. Recording/Reproducing capability is also included in the information collection system.

Empty

Design .... Combat ... Max takeoff Max landing

LB L.F.

6258 9500 9500 9500 9500

Output Rating/SL Sfcff SFÇ RPM Mil 1400* 0.580 6300 NRP 1250* 0.598 6040



AIRFRAME: TM55-1500-219-MTF. TM55-1520-210-10 TM55-1520-210-20 & 34 TM55-1520-210-23P

TM55-1520-210-PMS ENGINE:

TM55-2840-229-23' TM55-2840-229-23P DMWR 55-2840-113

DEVELOPMENT

Date of contract, MIPR Contracting agency No. of test aircraft First flight (scheduled) Completion of test and evaluation.. Contract delivery schedule

FUEL AND OIL

23 Jun 75 NARF Pensacola 1 4 Aug 77 16 Mar 77 1 Jun 78

Fuel: Grade . . Spec .... No. tanks:

Fuselage Ferry ..

Total qty Oil:

Spec ...

JP-4/5 MIL-T-5624

(2) 209 gal (1)300 gal 509 pi

MIL-L-23699 or

MIL-L-7808 No. tanks 1

FEATURE PERSONNEL

Crashworthy Fuel System Retractable antennas Environmental control system

Pilot Copilot Mission Operators

1 1 2

Location Fuselage Qty 4-1/2 gal

AVIONICS / ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS / NSN

NSN, 1520-00368-8442 LINE K 30548 COST, $1.920.000

o

FM 101-20

f FM 101-20

DIMENSIONS

Rotor dia Length:


Rotors Static.. Fuselage.. ! Span (max

Lateral). Height. Tread .. Gnd clearance

(static, against stops)....-.....

48 Ft.

.... 57 Ft. 1 In.

.... 57 Ft. 1 In. 41 Ft 11-1/4 In.

9 Ft. 4 In. . 14 Ft. 5-1/2 In. .. 8 Ft. 6-1/2 In.

6 Ft. 6 In.

r-9 FT 13/32 IN

8 FT 6-39/64 IN.

1 FT. 9 IN.

9 FT 4 IN.

o> 48frTr

D

2 FT 6-1/2 IN.—

44 FT 10-3/32 IN.

11 FT 8-21/32 IN.

8 FT6 IN

5 C3 CÍ uS 11 FT 9-3/4 IN J □ □

1 FT 3 IN GROUND LINE DESIGN GROSS WEIGHT

40 FT 7-3/32 IN. 41 FT 11-5/32 IN.

1-102 Figure 1-32. Principal Dimensions EH-IX (Quick Fix 2)

1-103

1-58. EH-1X(Quick Fix 2) Characteristics

ENGINE

No. & model ..

Mfr Type Red. gear ratio Tailpipe Augmentation

(DT53-L-

Lycoming 104.33 / 0.312 Fixedarea None -,

13B

ENGINE RATINGS

T53-L-13B Output

Rating/SL SHP SFC RPM Mil ' 1400* 0.580 6300 NRP. 1250* 0.598 6040



AIRFRAME: TM55-1520-210-10 TM55-1520-210-23 TM55-1520-210-23P TM55-1520-210-PMS engine; TM55-2840-229-23 TM55-2840-229-23P DMWR 55-2840-113


MFRS MODEL: BELL 205 The Phase II QUICK FIX system is an airborne intercept,

jamming & direction finding (DF) system. The system is designed to have up to 3 A/C operating simultaneously. Each A/C has the capability to initiate DF action on a target. During multiple A/C operation, DF commands are transmitted via a secure digital data link, to command the other A/C to take DF bearings on the same target. Resulting Lines of Bearing & A/C position are returned to the initiating A/C via the same data link. The EH-1X is a modified UH-1H using the basic airframe, components and powerplant.

DEVELOPMENT

Date of Contract Jan 75 No of Test Aircraft 1 Follow on evaluation July 80

FEATURES

30 KVA Alternator Flight Limitations Airspeed — 90 KTS Max Bank Limits —30° Crash Worthy Fuel System Lightweight Avionics

PERSONNEL

WEIGHTS

Pilot Copilot Mission Operators

LB L.F. Empty

6258 Design 9500 Combat 9500 Max takeoff 9500 Max landing 9500

FUEL AND OIL

Fuel: Grade JP4/5 Spec MIL-T-5624 No. tanks:

Fuselage (2) 209 gal Ferry '(1)300 gal

Total qty 509 gal OU:

Spec MIL-L-23699 or


AVIONICS / ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS / NSN

NSN 152001042-9396 LINE,'H30829

cost, $1,920,000 •

FM

101-20

1-104 1-59. Loading and Performance — Typical Missions, UH-1V, EH-1H and EH-1X (Iroquois).

CONDITIONS

TAKEOFF WEIGHT (lb)

Fuel at 6.5 Ib/gal (grade JP-4) (lb)

Payload (outbound), (lb)

Payload (inbound). (lb)

Takeoff power loading^/. . (Ib/SHP)

Disk loading (lb/sq. ft)

Autorotation speed (min R/D) (kn)

Takeoff ground run at SL (6600 rpm)!V (ft)

Takeoff to clear 50 ft (6600 rpm)I/. . . . (ft)

Vertical rate of climb at SL (6600 rpm)L/ (fpm)

Maximum rate of climb at SL!/ (fpm)


Time: SL to 5000 ft 2/. (min)

Time: SL to 10,000 ft 2 ^min^

Service ceiling (100 fpm)2/ (ft)

Absolute hovering ceiling (6600 rpm)i/. (ft)

COMBAT RANGE (nmi)

Average cruise speed _. . (kn)

Cruising altitude (initial) (ft)

Cruising altitude (final) (ft)


COMBAT RADIUS !S( (nmi)

Average cruise speed. (kn)

BASIC

(PERSONNEL

CARRIER)

7644 i/

1370

800

0

6.94

.4.22

61

0

0 .

1620

1653

61

3.1

6.2

18,340

14,800

.275 ..

Ill

2000-4000 .

2000-4000

2.46

141

111

TRANSPORT

(CARGO OR

TROOP)

9264i/

1370

2420

0

8.42

5.11

65

0

0

420

1126

65

4.6

9.9

13,960

, 400°.

„■ 250

105

2000-4000

20004000

2.37

124

107

LITTER

EVACUATION

7414.5/

1370

0

1500 9/

6.74

4.10

60

0

0

1960

1691

60

2.9

5.9

19,140

16,000.

FERRY

9305 5/

33202/

0

0

. ,8,45

5.14

65

0

0

580

1112

65

4.1

10.2

13,640

3600

676

110

20004000

20004000

6.13

133

121

FM 101-20

1-105

• • 1-59. Loadingand Performance — Typical Missions, UH-1V, EH-1H and EH-1X(Iroquois)(CONT).

CONDITIONS

BASIC

(PERSONNEL

CARRIER)

TRANSPORT

(CARGO OR

TROOP)

LITTER

EVACUATION FERRY

Cruising altitude (outbound) (min/max) (ft)

Cruising altitude (inbound) (ft)


FIRST LANDING WEIGHTS/.- (lb)

Ground roll at SL (6600 rpm) (ft)

Total from 50 ft (6600 rpm) (ft)

COMBAT WEIGHTS/ (lb)

Combat altitude (ft)

Combat speed!/. (kn)

Combat climbl/. (fpm)

Combat ceiling (5Q0 ft/min)!/ (ft)

Service ceiling (100 ft/min)2/ (ft)

Absolute hovering ceiling (6600 rpm)!/ (ft)

Takeoff ground run at SL (6600 rpm)l/ (ft)

Takeoff to clear 50 ft (6600 rpm)!/ (ft)

Maximum rate of climb at SlZ-/. (fpm)


Max speed at SLl/ (kn)

Basic speed at 5000 ftl/. (kn)

LANDING WEIGHTS/ (lb)

Ground roll at SL (6600 rpm) (ft)

Total from 50 ft (6600 rpm) (ft)

2000-4000

2000-4000

2.73

6997

0

0

6197

2000-4000

116

2256

23,550

24,070

21300

0

0

2232

55.9

120

120

6977

0

0

2000-4000

20004000

2.54

8584

0

0

6164

20004000

116

2276

23,694

24310

21,400

0

0

2251

55.8

120

120

... 8584

0

0

20004000

20004000

2.38

6789

0

0

8289

20004000

120

1370

15,960

16342

11,600

0

0

1399

62.0

120

120

6789

0

0

6316

120004000

- 116

2200

23,150

23,680

20,700

0

0

2178

56.1

120

120

6316

0

0 FM 101-20

1-106

1-59. Loadingand Performance — Typical Missions, UH-1V, EH-1H and EH-1X(Iroquois)(CONT).

JV Takeoff power.

lJ Normal rated power.

-2/ For RADIUS mission if radius is shown.

4/ Vne limit.



-2/ Includes two 150-gallon ferry tanks.

Based on engine specification takeoff shaft horsepower.

-2/ Six 250-pound litter patients.

IS' Detailed descriptions of RADIUS and RANGE missions are same as shown in paragraph 1-38.

Performance Basis:

a. Reference operator’s Manual Army Model UH-1D H Helicopter TM 55-1520-210-10.

b. All data are at 6600 rpm unless otherwise noted.

FM

10

1-2

0

FM 101-20

1-60. Performance Notes, UH-1V, EH-1H and EH-1X (Iroquois).


Warm up, take off, climb on course to 2000-4000 eet initial altitude at normal rated power, proceed at

long range cruise speed to remote base, land, and unload passengers. Without refueling, warm up, take off, climb on course to 2000-4000 feet at normal rated power, and return at long range cruise speed. Range-free allowances are 4 minutes at normal rated power for warmups and takeoffs plus 10 percent of initial fuel for reserve.


Warm up, take off, and climb on course to 2000-4000 feet at normal rated power. Cruise climb on course at long range cruise speed to final altitude of 2000-4000 feet. Proceed at long range speed to remote base, land, and unload cargo or troops. Without refueling, warm up, take off, climb on course to 2000-4000 feet at normal rated power, and return at long range cruise speed. Range-free allowances are 4 minutes at normal rated power for warmups and takeoffs plus 10 percent of initial fuel for reserve.

climb on course to 2000-4000 feet at normal rated power, and return at long range cruise speed. Range-free allowances are 4 minutes at normal rated power for warmups and takeoffs plus 10 percent of initial fuel for reserve.

FORMULA: RANGE MISSION I

Warm up, take off, and climb on course to 2000-4000 feet initial altitude at normal rated power. Proceed at long range cruise speed to remote base and land. Range-free allowances are 2 minutes at normal rated power for warmup and takeoff plus 10 percent of initial fuel for reserve.


Warm up, take off, and climb on course to 2000-4000 feet at normal rated power. Cruise climb on course at long range cruise speed to final altitude of 2000-4000 feet. Proceed at long range cruise speed to remote base and land. Range-free allowances are 2 minutes at normal rated power for warmup and takeoff plus 10 percent of initial fuel for reserve.



Warm up, take off, and climb on course to 2000-4000 feet at normal rated power. Proceed at long range cruise speed to remote base, land, and pick up litter patients. Without refueling, warm up, take off,

Warm up, take off, and climb on course to 2000-4000 feet at normal power. Cruise climb on course at long range cruise speed to final altitude of 20004000 feet. Proceed at long range cruise speed to remote base and land. Range-free allowances are 2 minutes at normal rated power for warmup and takeoff plus 10 percent of initial fuel for reserve.

Source: DRSTS-WU DRCPM-AEL

1-107

FM101-20

/ i

y

'¿J

Figure 1-33. UH-60A (Blackhawk)

* 1-108

FM 101-20

7/ ■

DIMENSIONS

/ Rotor D.ia, 53 Ft. 8 In Length:

Rotors _ Operating 53 Ft. 8 In

.. . Static Fuselage 50Ft. 7.5 In

V 7

/ TURNING ■RADIUS

41 IN.-7.7 IN / Span (Max ; ■ t ^ ,

Lateral). ''.N 9 Ft. 8.6 In Height. : 17 Ft. 1 In Tread ’... 8 Ft. 10.6 In n

Ground Clearance Static 8 Ft. 9 In

□ Q

\ \ \ \

/ \ \

sv 11 FT-0 IN. ROTOR DIAMETER

(■

'N. I I

9 FT -5 IN. 8 FT -9 IN. ROTOR ROTOR TURNING STATIONARY

1

12 FT-5. IN.

r □□ -■b 6 FT -1 IN -A—■ 5 FT-0 IN.

3 FT -0 IN. I

12 FT-6 IN. WHEEL BASE 29 FT. -1.7 IN 11 FT-4 IN. 11 FT-1 IN.

Figure 1-34. UH-60A (Blackhawk) 1-109

1-110

1-61. UH-60A (Blackhawk) Characteristics

ENGINE

No. & model .. (2)T700-GE-700 Mfr General Electric Engine spec. no.

.. DARCOM-CP-2222-02000

Type Turboshaft

Length 46.5 In. Width 25 In. Height 23 In. Weight 415 Lbs.

ENGINE RATINGS

Standard Sea Level Conditions SHP RPM

Max Continuous 1240 20900 IRP 1543 20900

MISSION AND DESCRIPTION WEIGHTS

The Blackhawk helicopter will perform primary and secondary missions of transporting internal loads under visual and instrument conditions day and night and external loads under visual flight conditions.

The Blackhawk (UH-60A) is a twin engine rotary wing aircraft which will carry eleven (11) combat equipped troops and a crew of three (3). Optional seating allows up to 14 combat equipped troops. When used as an aerial medical evacuation vehicle it will accomodate 4 litter patients and a medical attendant. An external cargo hook with 8,000 lbs. load capacity and provisions for an internal high performance rescue hoist are also provided. The UH-60A is designed to operate in temperatures from —65°F to +125°F.

DEVELOPMENT

LOADING LB

Empty 10,500 Design Gross 16,450 Max Alternate 20,250

FUEL AND OIL

Fuel: Grade JP-4 Spec MIL-T-5624 Alternate JP-5 Emergency ..

TECHNICAL PUBLICATION Date of Contract First Flight (similar aircraft) First Production Aircraft... AIRFRAME:

TM55-1520-237-10 TM55-1520-237-23 TM55-1520-237-23-1 TM55-1520-237-23-2 TM 55-1520-237-23-3 TM 55-1520-237-23-4 TM 55-1520-237-23-5 TM 55-1520-237-23-6 TM 55-1520-237-23-7 TM 55-1520-237-23-8 TM 55-1520-237-23-9 TM55-1520-237-23-10 TM55-1520-237-23P TM11-1520-237-23-1 TM11-1520-237-23-2 TM 11-1520-237-23-3

ENGINE: TM55-2840-248-23 TM55-2840-248-23P

CAPACITIES

Cargo Apartment Floor

Length 110” Length (including crew chief station) 151” Width 72” Height 53.5”

Cargo Door Height 54” Width . 68”

Nov 1976 . Oct 1974 Aug 1978

No. Tanks 2 Location Rear Fuselage Qty 362 Gallons

PERSONNEL

Crew 3 Troops 11 (optional troop seatings).... 14

Oil: Engine Spec MIL-L-23699 Alternate MIL-L-7808 No. Tanks ... 1 Location Main Frame —

Engine Transmission:

Litters..., Attendant

!oh

4 1

;’5

Spec MIL-L-23699 Alternate MIL-L-7808

' 2'f

AVIONICS / ARMAMENT

Refer to cKaßfe 2. A

FLYAWAY

NSN 1520-01035-0266 LINE, K32293 COST $

1

• • • • • FM

101-20

1-62. Loading & Performance^ - Typical Missions, UH-60A (Black Hawk)

’ CONDITIONS COMBAT ASSAULT : SEA LEVEL

COMBAT ASSAULT 4000’/95°F

MAX ALT GROSS WT SEA LEVEL

MAX ALT GROSS WT

400Ö7Ö5F

FERRY MISSION STD DAY

NO OF TROOPS/PAYLOAD 11 14 11 14

2Estimated Gross Weight (lbs)

Payload (Outbound) (lbs)

Payload (Inbound) (lbs)

Vmax (IRP) (kts)

Max Cruize Speed (MCP) (kts)

Vcruize (Best Range) (kts)

Max Rate-of-Climb (IRP-Vbroc) (fpm)

Vert Rate-of-Climb (95% IRP) (fpm)

Service Ceiling (100 fpm) (ft) .

Service Ceiling (Single Eng) (ft)

Hover Ceiling (Oge, IRP) (ft)

Hover Ceiling (2 ft Wheel Ht, IRP) (ft)

ORadius of Action (nm)

Ferry Range (nm)

16700

2640

0

157

150

130

2735

1515

18,000

8700

9800

14800

106

17420

3360

0

156

149

130

2550

1220

17200

7500

8600

13600

105

16700

2640

0

156

137

135

2010

290

14000

3600

5000

9200

133

17420

3360

0

155

136

135

1840

13000

2400

4200

8400

133

20250

6195 I .

3000

1284

1214

1004

1645

13700

3000

4800

9600

904

20250

6195

3000

1294

1054

1054

1075

9800

4000

1104

IPerformance with IR Suppressor Installed. 2Empty Wt -10500 lbs. Fixed Useful Load with Crew of 3 - 935 lbs 38 Min Ground Time, 1 Min Hover, Climbout. Vcruise, 5 Min Noe at 40 Kts & Return with 30 Minute Reserve. ' 40utbound Payload is External 30ft2 Equivalent Flat Plate Area

19500

149

143

126

2045

14600

4200

5000

10400

950

Source: AVRADC0M - DRCPM-BH

FM 101-20

FM 101-20

i1

*•«?' ^íhim^saSk

X

J

Sfiâ

m

§

Figure 1-35. C-12A (Huron)

1-112

FM 101-20

43 FT 10 IN.

U 15 FT .5 IN

D OOOOO o

O=D

1 14.5 IN. ILt o

? 14 FT 11.5 IN.

29.6 IN

T5 ó il

\J

18 FT 5 IN.

DIMENSIONS

Wing Span 54 Ft. 6 In. Length 43 Ft. 10 In. Height 15 Ft. 5 In. Tread 17 Ft. 2 In. Prop Grd Clearance 1 Ft.

54 FT. 6 IN

-ft-

FT. 2.5 IN. DIA

17 FT 2 IN

Figure 1-36. C-12A (Huron) 1-113

1-114

1-63. C-12A (Huron) Characteristics.


No. and Model Mir Type Prop Mfg Prop Type — No. Blades ... Prop Dia

(2) PT6A-38 UACL Turbo Prop ... Hartzell C5 3 . 8 ft. 2Vi in.

ENGINE RATINGS

TAKEOFF SHP 750 ALT SL

Mfg. Model: Beech Aircraft Corp. A200

The C-12A is an off-the-shelf utility aircraft which is totally contractor supported.

The C-12A is an all metal twin turbo prop engine, fixed wing, pressurized cabin, passenger/cargo carrying aircraft. The aircraft is designed and equipped for flight operations under Instrument Flight Rule (IFR) conditions day or night into high density air traffic control zones and into known icing weather conditions.

DEVELOPMENT

Date of contract Aug 1974 First flight (Similar aircraft) TSARCOM First acft delivered Sept 1975

LOADING LB. Empty Bask Design 12,500 Combat

Clean Light Scout Heavy Scout Hog

Max. Takeoff Max. Landing 12,500

FUEL AND OIL

Fuel: Grade JP 4/5 Spec MIL-T-5624 No. tanks 12 Location 10 Wing

2 Nacelle Qty 386 (544 w/

Aux Tanks) TECHNICAL PUBLICATIONS

AIRFRAME:

Commercial Manuals (Contractor Supported)

ENGINE:

FEATURES PERSONNEL

All Metal T-Tail Retractable Tricycle with

Crew Passengers

Dual Main Wheel Dual Side by Side Flight Controls

Oil: Spec MIL-L-23699 No. tanks 2 Location Nacelle Qty 3.5 Gal Each Tank

AVIONICS/ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS / NSN Pratt and Manuals

Whitney Commercial

NSN 1510-01005-5461 LIN A29676 COSTS, $680,883

CM 101-20

FM 101-20

1-64. Performance — Typical Mission, C-12A (Huron).

.Payload. rù oRange '... :

cCruise Speed: ;. w cMax Speed . :

"Min Takeoff Distance . ^Min LandingDistance. . Rate of Climb (1 Eng) .

; Service Ceiling (2 Eng) • Service Ceiling ( 1 Eng).

.. (LB)

. (NMI) .. (KN) .. (KN) ...(FT) ...(FT) (FPM) .. (Ft) ... (Ft)

4764 @31,000 1177 Aux Tanks 1780

@25,000 24131,000 222 270

3824 2620

602 30,400

Source: DRSTS-WP

1-115

FM 101-20

m

Figure 1-37. OV-1 (MOHAWK)

1-116

12

FT 9

-3/4

IN.

FM 101-20

48 FT

UUQ /

10 FT

T 2 IN. STATIC

IS FT 10 IN. — DIMENSIONS

Wing: Area 360 Sq. Ft Span 48 Ft MAC 94.8 In Length 43 Ft. 11-1/2 In Height 12 Ft. 8 In Tread 9 Ft. 2 In

1 A ! n/Vn

n n \j

<2-

ü

—3 II FT 8-1/4 IN.

43 FT 11-3/8 IN

Figure 1-38. Principal Dimensions, 0V-1B and C (Mohawk)

1*117

FM 101-20

O

r

3

Figure 1-39. The 0V-1B (Mohawk) aircraft

1-118

1-119

1-65. OV-1B (Mohawk) Characteristics.

ENGINE, MISSION AND DESCRIPTION WEIGHTS

No. & model Mfr Type

Engine spec No Red. gear ratio . Prop mfr Blade design No No. of blades . Prop dia

. (2) T53-L-7

. Lycoming

. Free power turbine

. 104.21B & .11C

. 12.4

. Ham std

. 7125-6

. 3

. 10 ft

ENGINE RATINGS

Rating/SL Max (takeoff) MU NRP

Output

SHP SFC RPM 1100 0.670 1700 1000 0.679 1700 900 0.692 1700


AIRFRAME: TM55-1510-204-10/5 TM55-1510-204-CL/5 TM55-1510-204-20/1-1

& 20/1-2 TM55-1520-204-35-1 & 35-2 TM55-1510-204-23P1-P2-P3

ENGINE: TM55-2840-233-24 TM55-2840-233-23P

Mfr’s Model: Grumman

The primary mission of the OV-1B is electronic surveillance using the sidelooking airborne radar (SLAR). In addition, it is capable of performing missions of photographic reconnaissance, visual reconnaissance and observation, artillery gunfire spotting, air control, and radiological monitoring.

The OV-1B is a two-place, twin-turboprop aircraft capable of operating from small fields and unimproved runways. Design features include a midwing, three-taU configuration of semimonocoque construction equipped with wide span flaps.

The crew of two are seated side-by-side within a bubbled enclosure at the extreme forward end of the fuselage.

A remotely operated day-and-night KA-30 camera installation provides horizon-to-horizon photo coverage along the aircraft flight path.

The OV-1B carries an APS-94 side looking airborne radar antenna as standard equipment.

External provisions are incorporated to carry two 150-gallon fuel tanks or two resupply containers.

DEVELOPMENT

First flight (prototype) .. Estimated first service use

November 1961 January 1963

FEATURES PERSONNEL

Ejection Seats Low Physical Profile All Weather Opération

Capability Capable of Deployment to Distant MSN Area by Using Extended Range Tanks (300 gal)

Pilot Mission Operator

LB Empty E 10,983 Basic 11.217 Design 13,100 Combat (basic

mission) 12,882 Normal takeoff. 13,654 Max takeoff ... 16,643 Max landing ... 16,643

L.F.

4.0

FUEL AND OIL

Fuel: Grade JP-4 Spec MIL-T-5624

No. tanks: Fuselage . External . Total Qty

OU: Spec Qty

(1) 297 gal (2) 150 gal 597 gal

MIL-L-23699 5 gal

AVIONICS / ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS / NSN

NSN 1510-00-715-9379 COSTS $976,437 LIN A30221

FM 101-20

1-120

/

1-66. Loading and Performance - Typical Mission, OV-1B (Mohawk).

TAKEOFF LOADING CONDITION OBSERVATION,

NO STORES 1

NIGHT PHOTO, TWO A6

EJECTORS 3

EMERGENCY RESUPPLY,

TWO RESUPPLY CONTAINERS

5

FERRY, TWO 150-GAL

EXT TANKS 7

TAKEOFF WEIGHT (lb) Fuel internal/external (lb) Payload (lb) Wing loading (lb/sq ft) Stall speed (power-off) 4/ (kn) Takeoff run at SL - calm (ft) Takeoff to clear 50 ft - calm (ft) Max speed/altitude 4/ (kn/ft) Rate of climb at SL ^ (fpm) Time: SL to 20,000 ft 2/ (min) Time: SL to 25,000 ft 2/ (min) Service ceiling (100 fpm) 2/ (ft) COMBAT RANGE J/ (nmi)

Average cruising speed (kn) Cruising altitude (s) (ft)

Cruise time (hr) Mission time (hr)

13,654 1930

38 73

995 1625

240.5/12,500 2800

9.5 15.5

29,500 365 200

5000 1.80 1.84

13,915 1930 264

38.7 73.8 1040 1690

238/12,000 2700

10 16

28,750 358 200

5000 1.77 1.80

15,168 1930 1500 42.1

77 1270 2000

226.8/10,000 2320

13 23

26,500 334 200

5000 1.64 1.69

15,918 1930/1950

44.6 79

1410 2185

226/8000 2160

15 26.5

24,900 1053 203

20,000 4.98 5.30

COMBAT LOADING CONDITION NO STORES 2

TWO A6 EJECTORS

4


6

COMBAT WEIGHT (60 percent internal fuel). (lb) . Engine power Fuel (lb). Combat speed/combat altitude 2/.... (kn/ft) . Rate of climb/combat altitude 2/.... (fpm/ft) Combat ceiling (500 fpm) 2/. (ft) . Rate of climb at SL 2/ (fpm) . Max speed at SL 2/ (kn) . Max speed/altitude 2/ (kn/ft).

LANDING WEIGHT (10 percent internal fuel) (lb) . Fuel .... 7 (lb) . Stall speed-power-off/approach power .. (kn) . Landing distance clear 50-ft obstacle ... (ft) .

12,882 Military

1158 250/5000

2660/5000 27,700

3050 247.2

252/11,500 11,917

193 67.5/54.6

870

13,143 Military

1158 248/5000

2560/5000 26,900

2940 244.9

249.5/11,500 12,178

193 68.2/55.2

890

14,396 Military

1158 238/5000

2175/5000 23,800

2530 235.9

239.5/10,000 13,431

193 71.5/58

1330

i

FM 101-20

1-66. uVl'.

Loading and Performance ,— Typcial Mission, 0V-1B (Mohawk) (CONT). U' -uL

-1/ Normal rated power.

-2/Military rated power.

-2/See notes on mission specifications. '

4/Flight idle power, propeller control at max rpm.

►2/Power for level flight at 120 percent of stall speed, power off, propeller control at max rpm.

Source: DRCPM-AEL(2)

• •

}

î *•

FM 101-20

1-122

1 -67. OV-1C (Mohawk) Characteristics.


No. & model Mfr Type. .......

Engine spec No

Red. gear ratio Prop mfr No. blades . . Blade design No Prop dia

.(2) T53-L-7/15

. Lycoming

. Power free turbine

. 104.11C, .21-B and .35

. 12.46

. Ham std

.3

. 7125-6

. 10 ft

ENGINE RATINGS

T53-L-7

Rating/SL Max (takeoff) Mil . . NRP

T53-M5

Rating/SL MU NRP

Output SHP SEC RPM 1100 0.670 1700 1000 0.679 1700 900 0.692 1700

Output SHP SFC RPM

1160* 0.620 1700 1000* 0.650 1600

*Mechanical limited.


Mfr’s Model: Grumman

The primary mission of the OV-1C is to perform Infrared (IR) reconnaissance missions using the Infrared sensor. In addition it is capable of performing photographic missions, visual reconnaissance and observation, artillery gunfire spotting, air control, and radiological monitoring.

The OV-1C is a two-place, twin-turboprop aircraft capable of operating from small fields and unimproved runways. Design features include a midwing, three-tail configuration of semimonocoque construction equipped with wide span flaps.

The crew of two are seated side-by side within a bubbled enclosure at the extreme forward end of the fuselage.

A remotely operated day-and night KA-30 ór KA-76 camera installation provides horizon-to-horizon photo coverage along the aircraft flight path. A nose-mounted KA-60, 70-mm panoramic camera is also provided. The OV-1C carries AN/ASS14 infrared detection equipment.

The infrared surveillance system makes it possible to detect military terrestrial targets by inherent characteristics that are distinguishable in the visual and infrared portion of the electro- magnetic spectrum.

External provisions are incorporated to carry two 150-gallon fuel tanks or two resupply containers.

LB Empty ........ 10,011 Basic 10,379 Design 11,924 Combat (basic

mission) 12,296 Normal takeoff . 12,682 Max takeoff ...15,302 Max landing ... 15,302

FUEL AND OIL

Fuel: Grade JP-4 Spec MILT-5624 No. tanks:

Fuselage (1) 297 gal External .... (2) 150 gal


L.F.

4.9/4.0

Spec MIL-L-23699 Qty 5 gal

AVIONICS / ARMAMENT DEVELOPMENT :

Refer to chapter 2. March 1961 July 1961 FLYAWAY COSTS / NSN

First flight (prototype) First service use

AIRFRAME: TM55-1510-204-10/4 TM55-1510-204-CL/4 TM55-1510-204-20/1

& 20/1-2 TM55-1510-204-35-1 6r35-2 TM55-1510-204-23P1-P2-P3

ENGINE: TM55-2840-233-24 TM55-2840-233-23P

FEATURES PERSONNEL

E j ection Seats Pilot Low Physical Profile Mission Operator All Weather Operation

Capability

Capable of Deployment to ; : / Distant MSN Area by Using ; f. Extended Range Tanks (300 gal)

NSN 1510-00715-9380 LIN A30271 COSTS $1,058,540

■'.// • ■ <'A i i ! r v yo

t *

FM

101-2

0

1-123

1-68. Loading and Performance — Typical Mission, OV-1C (Mohawk).

v ' 1>

TAKEOFF LOADING CONDITION

TAKEOFF WEIGHT (lb) • Fuel ; : (lb) Payload •. (lb) Wing loading (Ib/sq ft) Stall speed (power-off) 4/ (kn) Takeoff run at SL - calm-^ (ft) Takeoff run at SL - 25-kn wind & (ft) Takeoff to clear. 50 ft - calm-^ (ft)

: Max speed/altitude-i/ (kn/ft) Rate of climb at SL... ! (fpm) Time: SL to 20,000 ft 2/. ^ (min) Time: SL to 25,000 ft-1*2/ (min) Service ceiling ( 100 fpm) 2/ (ft) COMBAT RANGE -2/ (nmi)

Average cruising speed (kn) Cruising altitudes) (ft)

Cruise time ■ (hr) Mission time (hr)

OBSERVATION NO STORES

1

12,682 1930

38.4 74

990 613

1640 246/10,000

2270 14/12 24/20

26,200/27,450 408 200

5000 2.01 2.05

NIGHT PHOTO, TWO A6

EJECTORS 3

12,943 1930 264

39.2 74

1040 640

1680 243/10,000

2175 15/13 27/22

25,700/26,500 397 200

5000 1.96 2.00

EMERGENCY RESUPPLY


5

14,197 1930 1500

‘ v 43.0 78

1270 802

2000 229/5000

1800 22/17 47/35

21,600/23,200 362 200

5000 1.78 1.83

FERRY, TWO 150-GAL

EXT TANKS 7

14,961 3880

45.3 80

. 1440 930

2230 230/SL

1630 27/22 64/47

20,200/21,300 1081 215

20,000 4.72 5.17

COMBAT LOADING CONDITION

COMBAT WEIGHT (60 percent internal fuel).. Engine power

NO STORES 2

TWO A6 EJECTORS

4


6 (lb).. 11,910 12,171 13,425

Military Military Military Fuel (lb) Combat speed/combat altitude 2/ (kn/ft) Rate of climb/combat altitude 2/ (fpm/ft) Combat ceiling (500 fpm) 2/ (ft) Rate of climb at SL 2/ (fpm) Max speed at SL 2/ (kn) Max speed/altitude 2/ (kn/ft)

LANDING WEIGHT (10 percent internal fuel) .. (lb) Fuel (lb) Stall speed-power off 4/ /approach power-5/ . (kn) Landing distance to clear 50-ft obstacle (ft)

1158 256/5000

2100/5000 25,200

2880 255

256/10,000 10,945

193 68/54

850 2^

1158 252/5000

2000/5000 24,300

2780 252

253/10,000 11,206

193 69/55

870^

1158 240/5000

1620/5000 20,400

2320 239

240/5000 12,460

193 72/58

1335 S'

FM

101-20

1-124 1-68. Loading and Performance — Typical Mission, OV-1C (Mohawk) (CONT).

-M'Jormal rated power.

-^'Slilitary rated power.

^/See notes on mission specifications.

á/Flight idle power, propeller control at max rpm.

J/Power for level flight at 120 percent of stall speed, power off, propeller control at max rpm.

i/Takeoff distances are based on takeoff and obstacle speed equal to 120 percent of power-off stall

speed in takeoff configuration.

^Landing distance is based on approach speed equal to 110 percent of landing stall speed with rate of

sink equal to 14 fps.

-^Landing distance is based on approach speed equal to 110 percent of landing stall speed, power off,

with rate of sink equal to 8 fps.

FM 101-20

FM 101-20

1-69. Performance Notes, OV-1B and C (Mohawk).

FERRY MISSION (Column 7, paragraph 1-74).

TACTICAL AIR OBSERVATION MISSION AND NIGHT PHOTOGRAPHY (Columns 1, 3, and 5, paragraph 1-74).

Warm up, taxi, take off, climb on course to 5000 feet at normal rated power, and cruise at 200 knots at 5000 feet until all but reserve fuel is consumed. Range-free allowances are 5 minutes at normal rated power for warmup, taxi, and take off, plus 10 percent of initial internal fuel for reserve.

Warm up, taxi, take off, climb on course to altitude for maximum range at normal rated power, cruise at altitude and velocity for maximum range until all but reserve fuel is consumed, and drop external fuel tanks when empty. Range-free allowances are 5 minutes at normal rated power for warmup, taxi, and take off, plus 10 percent of initial fuel for reserve.

Source: DRCPM-AEL

1-125

FM 101-20

Figure 1-40. OV-1D (Mohawk)

1-126

FM 101-20

48 FT

TAIL SPAN 15 FT 10 IN.

HORIZ WL 100

WO y

10 FT WL 9

WL 0.0

BL 0.0

STATIC TREAD - 9 FT 1.9 IN.-

DIMENSIONS

Wing Area 360 Sq. Ft. Span 48 Ft. MAC 98 Ft. Length 41 Ft.

3.65 In. Height 12 Ft. 8 In. Tread 9 Ft. 2 In.

VERTICAL REF LINE STA5.75

HORIZ WL 100

(HORIZONTAL REF LINE)

13 FT

12 FT 8 IN a D □ q © STATIC GL 5 39 MIN

STATIC WHEELBASE 11 FT 8.2 IN.

MAX LENGTH -41 FT. 3.65 IN.

(SLAR ANTENNA INSTALLED) 43 FT 3.25 IN.

Figure 1-41. Principal Dimensions, OV-1D (Mohawk)

1-127

1-128 1-70. OV-1D (Mohawk) Characteristics.

(ENGINE MISSION AND DESCRIPTION WEIGHTS

No. & model (2) T53-L-701

Mfr Lycoming

Type Free power Turbine

Engine spec No 104.39

Red. gear ratio 12.38

Prop mfr Ham std

Blade design No 5157C-6

No of blades .. ' 3

Prop dia 10 ft

ENGINE RATINGS

T53L-701 Output Rating/SL SHP SFC RPM

MIL

NRP

1400 .590 1650

1250 .610 1590

TECHNICAL PUBLICATIONS AIRFRAME:

TM55-1510-213-10 TM55-1510-213-CL TM55-1510-213-23-1-2-3 TM-55-1510-204-23P1-P2-P3 'TM55-1510-213-PMS

ENGINE: TM-55-2840-233-24 TM-55-2840-233-23P

The primary mission of the OV-1 D is to perform either

infrared (IR) reconnaissance or side looking airborne radar (SLAR) missions. The SLAR and IR are

interchangeable. In addition, it is capable of performing photographic missions, visual reconnaissance and observation, artillery. gunfire

spotting, air control, and radiological monitoring. The

OV-1D is a two-place, twin turboprop aircraft capable of operating from small fields and unimproved

runways. Design features include a midwing, three-tail configuration of semimonocoque construction equipped with wide span flaps.

The crew of two are seated side-by-side within a bubbled enclosure at the extreme forward end of the fuselage.

The OV-1D is equipped with three independent photographic systems, all of which have automatic exposure controls and can be operated by either the pilot or observer.

External provisions are incorporated to carry two 150-gallon fuel tanks, two ECM pods, or LS 59A photo flasher.

FEATURES

Ejection Seat’s Low Physical Profile * All weather operation

capability Capable of deployment

to distant msn area by using extended range tanks (300 gal)

PERSONNEL

Pilot. 1 Mission Operator 1

Refer to Loading and Performance Chart. (Par 1-71)

FUEL & OIL

Fuel

Grade JP-4/5

Spec MIL-T-5624 No. tanks Fuselage (1) 297 gal External (2) 150 gal

Total qty 597 gal Oil: Spec MIL-L-23699 Qty 5 gallon

AVIONICS/ARMAMENT

Refer to Chapter 2.

FLYAWAY COSTS/NSN

NSN 1510-00869-3654 LIN A30296 COSTS $2,033,066

FM 101-20

FM 101-20

=53

v>

G

OPTIONAL EQUIPMENT

Figure 1-42. RV-1D Aircraft

1-129

FM101-20

576

190 TA L SPAN

'o' HORIZ WL 100

120 WL9

NOTE:

DIMENSIONS ARE IN INCHES

WL 0.0

BLO.O

STATIC -TREAD-

109.956

(RV-1D) STA-3.50 (OV-1D) STA-5.75 —

ST A 0.00

VERTICAL REF LINE

152 HORIZ WL 100

(HORIZONTAL REF LINE) ° O

STATIC WHEELBASE I cwrTH 495.65 (OV-1D) V40J2____JI-i MAX LENGTH«^ i0)

MAXLENGTH

MAX HORIZONTAL 490.69 (OV-1D) MAX HORIZONTAL 488.44 (RV-1D)

MAX HORIZONTAL 519.25 (WITH SLAB ANTENNA INSTALLED)-

Figure 1-43. Aircraft Dimensions

1-130

1-131

1-71. RV-1D (Quick Look)i

ENGINE

No. & model (2) T53-L-701

Mfr Lycoming

Type Free power Turbine

Engine spec No 104.39

Red. gearratio 12.38

Prop mfr Ham std

Blade design No 515706

No. of blades 3

Prop dia 10ft

ENGINE RATINGS

T53L-701 Output Rating/SL SHP SFC RPM

MIL 1400 .590 1650

NRP 1250 .610 1590


AIRFRAME: TM55-1510-213-10 TM55-1510-213-CL TM55-1510-213-23-1-2-3 TM55-1510-204-23P1-P2-P3 rrM55-1510-213-DMS

ENGINE: TM 55-2840-233-24 TM 55-2840-233-23P


The Quick Look II system provides an electronic location and identification capability operation in a tactical environment. The RV-1D is a two-place, twin turboprop aircraft capable of operating from small fields and unimproved runways. Design features include a mid-wing, three-tail configuration of semimonocoque construction. Large area flaps and droop ailerons are installed for added lift/drag requirements.

DEVELOPMENT

Date of contract Jql 75 Contracting agency Grumman & UTL No. of test aircraft 2 First flight scheduled Mar 77 Completion of test & eval DT/OT III 15 Nov 77 Follow on tests 30 Apr 78 Contract delivery schedule Jul 77

FEATURES

Ejection Seat’s Low Physical Profile All weather operation

capability Capable of deployment

to distant msn area by using extended range tanks (300 gal)

PERSONNEL

Pilot 1 Mission Operator 1

WEIGHTS

Refer to Loading and Performance Chart. (Par 1-71)

FUEL & OIL

Fuel * Grade JP-4/5 Spec MIL-T-5624

No. tanks Fuselage (1) 297 gal External (2) 150 gal Total qty 597 gal

OU: Spec MIL-L-23699 Qty 5 gallon

AVIONICS/ARMAMENT

Refer to Chapter 2.

FLYAWAY COSTS/NSN

NSN 1510-00368-8440 LIN A30 444 COSTS $2,886,664

FM 101-20

THIS PAGE LEFT BLANK INTENTIONALLY.

1-132

FM 101-20

1-72. loading & Performance - Typical Mission RV-1D (Mohawk)

TAKEOFF LOADING CONDITION

MAX GROSS WT. WITH AN/ALQ133 AND AN/USQ 61 NO EXT FUEL TANKS

MAX GROSS WT. WITH AN/ALQ 133 AND AN/USQ 61 EXT FUEL TANKS

Take Off Weight (lb) Weight Empty (lb) Payload (usefubSV (lb) Fuel (Internal) (lb) Stall Speed (Power Off)i_/ (kn) Take Off Run at SL-Calm 6À50C (ft) Take Off Run at SL-25 Kn Head Wind fiZl50C (ft) Take Off to Clear 50ft - Calm 6/l5°C (ft) Max Speed/Altitude (kn/ft) Rate of Climb at SL U (fpm) Timp: SL to 20,000 ft 1ÈJ (min) Time: SL to 25,000 ft lJ2J (min) Service Ceiling (100 fpm) i/?/ (ft) Combat Range ü/ (nm) Average Cruising Speed (kn) Cruise Altitude (5) (ft) Cruise Time .3/ (hr)

15,532 11,905 3,027 1,930

80 1,300

975 1,900

215/5000 2,500 13/10 22/17

25,000 355-

180 5,000

1.9

17,482 11,905 5,577 3,880

94 2,400 1,800

. 2,400 214/500

2,200 16/12 29/22

25,000 710 180

5,000 38

COMBAT LOADING CONDITION

Combat Weight (60% Internal Fuel) (lb) Engine Power (Prop RPM, Eng Torque Press) (rpm/lb) Fuel (lb) Rate of Climb/Combat Altitude (fpm/ft) Combat Ceiling (500 fpm) (ft) Landing Weight (10% Internal Fuel) (lb) Fuel (lb) Stall Speed-Power-Off Âpproach Power ü/ (kias/kn) Landing Distance to Clear 50ft Obstacle (ft)

14,760 1720/122

1158 1800/5000

25,000 13,795

193 78/70 2,000

16,710 1720/122

3108 1500/5000

25,000 13,795

193 78/70 2,000

1-133

1-134

1-72. Loading and Poriormanca - Typical Mission, OV-1D (Mohawk) (CONT).

-i/ Normal rated power.

-2/ Military rated power.

U See Mission Type. Sample is based on:

a. 5000 ft altitude. . - , b. Standard day. c. 180 knots CAS. ' , d. All stores installed. - e. Full external fuel, if installed. f. Total fuel consumption, with 10% reserve remaining. g. A total mission distance, from point of origin and return.

■5/Flight idle power, 0°-Bank, 15® flaps KIAS

Power for level flight at 120 per cent of stall speed, power-off, 15° flaps KT.

-5/ Takeoff distances are based on takeoff and obstacle speed equal to 120 per cent of power-off stall speed in takeoff configuration.

■2/ Landing distance based on a ground and air distance total at sea level approach speed equal to 120 per cent of landing stall speed or a CAS of 90.5 knots, ambient temp or 20°C, 0 knot head wind and 12.2 FPS rate of sink.

^ Landing distance based on a ground and air distance total, at sea level approach speed equal to 120 per cent of landing stall speed or a CAS of 98 knots, ambient temp of 20°C, 0 knot head wind and 12.2 FPS rate of sink.

Fuel and mission essential equipment.

Source: DRCPM-AEL (2)

FM 101-20

15003

Figure 1-44. T-41B (Mescalero)

1-135

FM 101-20

CS a n 5 DEC

25 FT6IN

smi IN.

11 FT 4 IN.

DIMENSIONS

Wing span 36 Ft. 2 In. Height 8 Ft. 11 In. Tread 7 Ft. 2 In.

r 8 FT 4 IN.

36 FT 2 IN.

i im r 6 FT4 IN.

7 FT 2 IN

Figure 1-45. Principal Dimensions, T-41B (Mescalero)

1-136

1-137

• • 1-73. T-41B (Mescalero) Characteristics.


No. & model (1)10-3600 Mfr Continental Prop type CS, VP Prop dia 6 ft, 4 in.

ENGINE RATING

Takeoff Normal

BHP RPM

210 2800 210 2800


AIRFRAME: TM 55-1510-212-10


ENGINE:

Commercial Manual

Mfr’s Model: Cessna 172

The T-41B is an interim inventory fill to replace O-l drawdown pending availability of the OH-6A. Missions include primary and advanced contact trainer and installation support roles. The T-41B will be used in two configurations as follows:

Utility mission — FAA normal category to include aircraft empty weight, including electronics, crew of two (instructor and student), at 200 pounds each, and fuel for endurance for 4.5 hours at 110 knots.

Normal mission — FAA normal category to include aircraft empty weight, including electronics, crew of one, two passengers, at 200 pounds each, and fuel for endurance for 4.5 hours at 110 knots.

DEVELOPMENT

Date of contract 8 August 1966 First Production acft October 1966

FEATURES

All metal. High wing. Fixed tricycle landing gear. Dual side-by-side controls.

PERSONNEL

Crew Instructor pilot Student pilot ..

or Crew Passengers

2 1 1

1 2

LB Empty 1545 Utility 2200 Normal 2500

FUEL AND OIL

Fuel: Grade 115/145 Spec MIL-G-5572 Qty 52 gal

Oil: Spec Temps above +40° F MHS-24A (SAE 50)

Temps below +40 F MHS-24A (SAE 30)

AVIONICS/ARM AMENT

Refer to chapter 2.

FLYAWAY COSTS/NSN

NSN 1510-00929-1012 LIN A30052 COSTS $16,200

FM 1

01-2

0

1-74. Performance — Typical Mission, T-41B (Mescalero)

Range (4.5 hours) (mi)..

Cruise speed J/.... ; ” (mph):

Max speed i (mph).

Takeoff distance '. . ......... (ft).

Landing distance . : (ft).

Rate of climb (fpm).

Service ceiling (ft).

590

148

.153

635

- 40Ó

910

17,500

i775 percent power at 5500 feet.

Source: DRSTS-WP

#

FMI 01-20

ig^ ' ‘ ï if»

TT"

Figure 1-46. T-42A (Cochise)

1-139

FM 101-20

37 FT 10 IN

6 FT6 IN

9 FT 7 IN

DIHEDRAL 6 DEG

V

DIMENSIONS

13 FT 9 IN

CD

Wing: Span 37 Ft. 10 In. Incidence (root) 4°

(tip) -Io

Dihedral 6° Sweepback 0.0°

Length 27 Ft. 3 In. Height 9 Ft. 7 In. Tread 9 Ft. 7 In. Prop and

clearance 10-1/2 In.

gnus 11 DEG

10-1/2

7 FT

Figure 1-47. PrincipEtl Dimensions, T-42A (Cochise)

1-140 i

1-141

1-75. T-42A (Cochise) Characteristics.

ENGINE

No. & model .... Mfr Engine spec No .. Prop mfr Blade design No .. Prop type Prop dia

(2) IO-470-L Continental 1634-B McCauley 78FF-0 Hyd.CS.FF 6 ft, 6 in.

No. blades 2

ENGINE RATINGS

BMP RPM ALT MIN Takeoff 260 2625 SL Cont. Normal 260 2625 SL Cont.


AIRFRAME: TM 55-1510-212-10


Mfr’s Model: Beech 95-B55B

The primary mission of the T-42A is the training of military pilots in instrument flying, in both day and night Instrument Flight Rule operations.

The secondary mission of the T-42A is twin-engine transition training of single engine rated pilots.

The T-42A is an all-metal, twin-engine, four place low wing monoplane, with retractable landing gear.

The cabin is designed to accommodate an instructor pilot and three student pilots. The instructor and primary student sit side by side; the two additional students sit immediately behind. The instructor and primary student each have a complete set of flight controls and instruments. The seating arrangement permits inflight movements of students from the forward primary seat to the rear seats.

Emergency evacuation is accomplished by quick-release jettison of windows on both sides of the windshield.

The warm air system is utilized for anti-icing, defrosting, and defogging of windshield.

DEVELOPMENT Commercial Manuals

(Contractor Supported)

ENGINE:

Commercial Manual

Date of contract February 1965 First flight July 1965 First acceptance August 1965 Production completed June 1966

FEATURES PERSONNEL

Cabin air conditioning, heating, and ventilation.

Cabin soundproofing. Oxygen system. Dual controls and instruments. Steerable nose wheel. Fuel injection. Propeller anti-icing and wing

and stabilizer deicing. Rotating beacon. Three-axis trim.

Crew 4 Instructor pilot 1 Student pilot 3

or Crew 1 Passengers 3

WEIGHTS

LB L.F. Empty 3423 Basic 3480 Design 5100 +4.4,

-3.0 Max takeoff .... 5100 do Max 5100 do

FUEL AND OIL

Fuel: " Grade 115/145 Spec MIL-G-5572 No. tanks 4 Location Wing Qty 136 gal

OU: Spec Temps above +40° F MHS-24A (SAE 50)

Temps below +40° F MHS-24A (SAE 30)

Location Engines Qty 6 gal

AVIONICS/ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS/NSN

NSN 1510-00872-7908 LIN A 30596 Costs,

$102,907

FM

101-2

0

FM 101-20

1-76- Loading and Performance - Typical Mission, T-42A (Cochise).

TAKEOFF LOADING CONDITIONS

Takeoff weight Fuel Payload Wing loading Stall speed-i' Stall speed-2/ Takeoff run at SL ... Takeoff run to clear 50 ft Max speed SL Rate climb SL Time SL to 10,000 ft Service ceiling (100 FPM)

BASIC MISSION

(lb) (lb) (lb) (lbs/sq ft) . . . .

(M (kn) (ft) (ft) (kn)

(fpm) (min)

(ft)

5,100 816

25.5 68

76.5 910

1,255 205

1,670 8

19,700

LANDING WEIGHT

(10% Fuel) 4,333

Fuel Ground roll at SL Landing distance to clear 50 ft obstacle

(lb) (ft) (ft)

85 8.05

1,580

-1/ Zero thrust, flaps 28°, and gear down -2/Power OFF, flaps up, and gear up

Source: DRSTS-WP

1-142

FM 101-20

-a . j'-'"" ,

W-A - -? ' .< ■'/*'-v

" . '.'-¿»¿iï-'.-1 ■

•* ' '/-‘fy ~ •

I

Figure 1-48. U-8D and G (Seminole), typical, (minor differences apparent between D and G models)

1-143

FM 101-20

45 FT 3-1/2 IN.

7 FT 9 IN

o C3

DIMENSIONS

Wing: Span 45 FT 3-1/2 In. Incidence (r;oot) 5°48 min Incidence (tip) 1° Dihedral 7° Sweepback 0.0°

Length 31 Ft. 6-1/2 In. Height 11 Ft 6-1/2 In. Tread 12 Ft. 9 In. Prop gnd

clearance 1 Ft. 3 In.

16 FT 4 IN.

31 FT 6-1/2 IN

[ t \

□□□ 's ✓ V ;

10 IN

CD 11 FT 6-1/2 IN

? 10 FT 9 IN.

Figure 1-49. Principal Dimensions, U-8D/G (Seminole)

1-144

1-145

1^^)-8D/^^ eminole) Characteristics.

ENGINE

No. & model.... (2) 0-480-1A/


Mfr’s Model: Beech E-50

Mfr Engine spec No .. Red. gear ratio .. Prop mfr Blade design No . Prop type

Prop dia No. blades Superch

-IB Lycoming 2202-B 0.642 Hartzell 10151-B8 Hydramatic, CS, FF 7 ft, 9 in. 3 1 stg, centrif

ENGINE RATINGS

BHP RPM ALT MIN Takeoff 340 3400 SL 5 Normal 320 3200 SL Cont.

The principal mission of the U-8D is the transportation of personnel, The U-8D is a clean Cantilever, low-wing monoplane and can be

quickly converted into a cargo carrier by removing the rear cabin seat and the right-hand front seat.

The cabin arrangement allows the front seat to accommodate three persons abreast, the pilot on the left, assist pilot or passenger in the center, and a passenger on the right, while the rear seat accommodates three additional passengers.

Emergency evacuation is accomplished by jettisoning the cabin door and by opening the rear cabin windows.

The leading edge, main spar, and rear section of the wings are joined by piano-type hinge loops and stainless steel rods.

Warm air system is utilized for anti-icing of windshields. The U-8D is similar to the U-8A and B, except it has three-

blade metal propellers in lieu of two-blade metal propellers plus increased horsepower and gross weight. All U-8A and B aircraft have been modified to U-8D aircraft.


AIRFRAME: TM-55-1510-201-10/3 (D/F) TM-55-1510-201-10/4 (DIG) TM-55-1510-201-10/5 (F) TM-55-1510-201-20 (D/G/F) TM-55-1510-201-20P (D/F/G) TM-55-1510-201-34P1 (D/G/F) TM-55-1510-201-34P2 (D/G/F) TM-55-1510-201-35 (D/G/F) TM-55-1510-201-CL/4 (D/G) TM-55-1510-201-2L/5 (F) TM-55-1510-201-ESC (D/G/F) TM-55-1510-201-PMS (D/G/F)

ENGINE: TM55-2810-218-10 TM55-2810-218-34 TM55-2810-218-34P

DEVELOPMENT

First flight First acceptance Production completed ... Formerly designated L-23D

FEATURES

Cabin heating, ventilation, and soundproofing.

Nonicing carburetors. Full-feathering props. Steerable nose wheel. Throw-over control column. Deicing equipment. Anticollision rotating beacon

light. Oxygen system.

October 1955 November 1956 October 1958

PERSONNEL

Crew 1 Passengers 5 Baggage compartment:

Aft 3001b Forward 262 lb

*U-8G incorporates a different seating arrangement, Airstairdoor, and extended cabin.

• • WEIGHTS

LB L.F. Empty (calculated).. 4944 Basic (calculated)... 4978 Design 7000 +4.4

-1.76 Combat (basic

mission) 5953 Max takeoff

(overload) *7300 Max takeoff

(normal) *7300 Max landing *?7000

•Limited by strength. ••Limited by max takeoff weight.

FUEL AND OIL

Fuill Grade Spec No. tanks ... Location .... Qty

Oil: Spec Temps above +606F .... Type II

Temps below +60°F Type III

No. tanks ... Qty

115/145 MIL-G-5572 8 Wing 230 gal

MIL-L-22851

MIL-L-22851

2 8 gal

AVIONICS/ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS/NSN

U-8D NSN 1510-00574-7938 LIN A30721 Costs, $115,250

U-8G NSN 1510-00912-4084 LIN 1430831 Costs, $114,687

FM 101-20

1-146

1-78. Loading and Performance - Typical Mission, U-8D/G (Seminole).

CONDmONS BASIC MISSION DESIGN MISSION NORMAL MISSION FERRY RANGE

TAKEOFF WEIGHT (lb) Fuel at 6.0 Ib/gal (grade 115/14S) (ft) Payload (outbound) (lb) . Payload (inbound) (lb). Wing loading (psf) . Stall speed (power oil) (land conflg) (kn).

■ Takeoff ground run at SL -i/ (ft). Takeoff to clear 50 ft 1/ (ft) . Rate of climb at SL 2/ (fpm) . Rate of climb at SL (one engine out) 2/ ... (fpm) . Time: SL to 10,000 ft 2/ (min). Time: SL to 20,000 ft 2/ (min). Service ceiling (100 fpm) 2/ (ft) . Service ceiling (one engine out) 2/ (ft) .

COMBAT RANGE (nmi) . Average cruising speed (kn) . Cruising altitude (ft). Total mission time (hr).

COMBAT RADIUS & (nmi). Average cruising speed (kn) . Cruising altitude (ft). Total mission time (hr).

FIRST LANDING WEIGHT & (lb) . Ground roll at SL (ft) . Total from 50 ft (ft).

COMBAT WEIGHT (ft). Combat altitude (ft). Combat speed 2/ (kn). Combat climb 2/ (fpm). Combat ceiling (500 fpm) 2/ (ft). Service ceiling (100 fpm) 27 (ft) . Service ceiling (one engine out) 27 (ft) . Takeoff ground run at SL -1/ (ft) . Takeoff to clear 50 ft 17 (ft). Rate of climb at SL 27 (fpm) .

7300^7

1380 682

None 26.4 75.0 1430 2385 1480

155 7.8

21.6 25,500

9500 1121

140 10,000

8.08 528 140

10,000 7.62

6630 1240 2018 5948

10,000 199

1550 24,100 29,700 10,900

830 1485 2010

7300^7

1062 1000 None 26.4 75.0 1430 2385 1480

155 7.8

21.6 25.500

9500 882 140

10,000 6.43 387 140

10,000 5.67

6768 1266 2063 5768

10,000 199

1620 25,000 30.500 11,100

750 1350 2090

730047

1380 682

None 26.4 75.0 1430 2385 1480

155 7.8

21.6 25,500

9500 912 171

10,000 5.45 430-5/ 172

10,000 5.10

6630 1240 2018 5948

10,000 199

1550 24,100 29,700 10,900

830 1485 2010

6618 4/

1380 None

23.9 71.5 1095 1900 1780 285 6.5

17.2 27.000 10.000

1185 139

10,000 8.55

5347 10,000

200 1765

26,500 31,700 11,600

2250

1-1

47

1-78. Loading and Performance - Typical Mission, U-8D/G (Seminole) (CONI).

CONDITIONS BASIC MISSION DESIGN MISSION NORMAL MISSION FERRY RANGE

Max speed at 9000 ft 2/ (kn) .. Basic speed at 50Ó0 ft^/ (kn) ..

LANDING WEIGHT (lb),. Ground roll at SL ...... . .^ (ft) .. Total from 50.ft .' Z. (ft) ..

200 192

5342 1000 1630

200 192

5445 1015 1640

200 192

5342 1000 1630

200 193

5347 1000 1630,

-i/Max power. METO power. For RÁDIUS mission if radius is shown.

& Includes crew of 1 at 200 lb. 65‘-percent METO power used for cruise.

Performance Basis: Phase IV flight test.

FM 101-20

FM 101-20

1-79. Performance Notes, U-8D/G (Seminole).


Warm up, take off, climb on course to 10,000 feet at METO power, cruise out at long range speeds to remote base, land, and discharge passengers and baggage. Without refueling, warm up, take off, climb on course to 10,000 feet at METO power, and return at long range speeds. Range-free allowances are 10 minutes of METO power for warmups and takeoffs, plus fuel for 20 minutes at speeds for long range at sea level, and 5 percent of initial fuel for reserve.


Warm up, take off, climb on course to 10,000 feet at METO power, cruise out at 65 percent power to remote base, land, and discharge passengers and baggage. Without refueling, warm up, take off, climb on course to 10,000 feet at METO power, and return at 65 percent power. Range-free allowances are 10 minutes of METO power for warmups and takeoffs, plus fuel for 20 minutes at speeds for long range at sea level, and 5 percent of initial fuel for reserve.

FORMULA: RANGE MISSIONS I, II, & IV

Warm up, take off, climb on course to 10,000 feet at METO power, and cruise out at long range speeds until only reserve fuel remains. Range-free allowances are 5 minutes of METO power for warmup and takeoff, plus fuel for 20 minutes at speeds for long range at sea level, and 5 percent of initial fuel for reserve.


Warm up, take off, climb on course to 10,000 feet at METO power, and cruise out at 65 percent power until only reserve fuel remains. Range-free allowances are 5 minutes of METO power for warmup and takeoff, plus fuel for 20 minutes at speeds for long range at sea level, and 5 percent of initial fuel for reserve.

GENERAL DATA

Engine ratings shown are engine manufacturer’s guaranteed ratings. Power values used in performance calculations for the 0-480-1 engine are as follows:

BMP RPM ALT MIN

Max 340 3400 SL 5

METO 320 3200 SL Cont.


Beech Aerodynamic Report 691, Performance Data for the USAF Standard Aircraft Characteristics Charts from Phase IV Flight Test of the L-23D Air- plane.

Beech Aerodynamic Report 725, U.S. Army Flight Manual Substantiating Data from USAF Phase IV Flight Tests (U-8D).

Source: DRSTS-WP

1-148

FM 101-20

S «1

AV

Figure 1-50. U-8F (Seminole)

1-149

FM 101-20

45 FT 10-1/2 IN

7 FT 9 IN

CT

12 FT 9 IN.

17 FT 2-3/4 IN.

33 FT 4 IN

)

[2 <3

1 ■=^7

DIMENSIONS

Wing: Span 45 Ft. 10-1/2 In. Incidence (root) 4°, 48 min Incidence (tip) 0.0° Dihedral.. ; 7° Sweepback:

Outer panel 25 percent chord 0.0°

Center section 100 percent chord 0.0°

Length 33 Ft. 4 In. Height 14 Ft. 2 In. Tread 12 Ft. 9 In. Prop gnd

clearance 10-1/2 In.

□an Cb

12 FT 3-1/2 IN.

. 8 FT 9 IN

14 FT 2 IN.

1-150

Figure 1- 51. Principal Dimensions, U-8F (Seminole)

1-151

1-80. U-8F(S«mino(e) Characteristics


No. & model .... (2) 0480-3A Mfr Lycoming Engine spec No .. 2228 Superch 1 stg, centrif Red. gear ratio ... 77:120 Prop mfr Hartzell Blade design No .. 10151-B8 Prop type Hyd, FF, CS No. blades 3 Prop dia 7 ft, 9 in. Augmentation ... Fuel injection

(3-piston type)

ENGINE RATINGS

BHP RPM ALT MIN Takeoff 320 3400 SL 5

340 3400 11,000 5 Normal 320 3200 SL Cont

320 3200 11,000 Cont


AIRFRAME: TM-55-1510-201-10/3 (D/F) TM-55-1510-201-10/4 (DIG) TM-55-1510-201-10/5 (F) TM-55-1510-201-20 (D/G/F) TM-55-1510-201- 20P (D/G/F) TM-55-1510-201-34P1 (D/G/F) TM-55-1510-201-34P2 (D/G/F) TM-55-1510-201-35 (D/G/F) TM-55-1510-201-CL/4 (D/G) TM-55-1510-201-CL/5 (F) TM-55-1510-201-ESC (D/G/F) TM-55-1610-201-PMS (D/F/G)

ENGINE: TM55-2810-218-10 TM55-2810-218-34 TM55-2810-218-34P

Mfg. Model: Beech

The principal mission of the U-8F is the transportation of personnel. The U-8F is a semimonocoque, low-wing monoplane easily converted

into a cargo carrier by removing the passenger compartment seats. The U-8F is similar to the U-8D except the larger fuselage is arranged

with separate crew and passenger compartments. The crew compartment is arranged with the pilot’s seat on the left and the copilot’s seat on the right of a center aisle. It is equipped with dual flight controls and is separated from the passenger compartment with sliding doors. The passenger compartment is arranged with two passenger seats on the left and two or three passenger seats on the right of the center aisle. The track-mounted seats facilitate removal or installation and permit versatile seating arrangements. The baggage compartment is located at the rear of the passenger compartment with access from the passenger compartment. The cabin access door on the left side of the fuselage, aft of the wing, incorporates stair-type steps and may be opened or closed and locked from either the inside or outside. A jettisonable escape hatch is located opposite the cabin access door. Powerplants feature fuel injection and manually selected, electrically actuated inlet air source selection.

DEVELOPMENT

First flight First delivery Production completed

FEATURES

Thermostatically controlled cabin heat.

Fresh air and oxygen outlets at each station.

Electrically actuated flaps. Convention^ flight controls,

manually operated. Steerable nose wheel. FuH feathering props. Hydraulically controlled brakes. Crossfeed fuel system. Windshield wipers. Deicing and anti-ice equipment.

August 1958 February 1959 December 1962

PERSONNEL

Crew 1 Passengers 5 Baggage compartment:

Floor 1501b Shelf 1501b

LB L.F. Empty (calculated) 5246 Basic (calculated).. 5282 Design 7700

Combat (basic) mission) 6276

Max takeoff: (overload) *7700 (normal) *7700

Max landing **7350

•Limited by strength. ••Limited by gear strength.

+6.6 -2.64

+6.6 -2.64

FUEL AND OIL

Fuel: Grade 115/145 Spec MIL-G-5572 No. tanks 8 Location Wing Qty 230 gal

Oil: Spec Temps above +60 r MIL-L-22851 Type II

Temps below +60° F MIL-L-22851 Type III

No. tanks 2 Qty 8 gal

AVIONICS/ARM AMENT

Refer to chapter 2.

FLYAWAY COSTS/NSN

NSN 1510-00701-2233 LIN A30821 COSTS, $144,593

FM

101-20

Ul IO 1-81. Loading and Performance - Typical Mission, U-8F (Seminole).

CONDITIONS BASIC MISSION

TAKEOFF WEIGHT (lb) ... Fuel at 6.0 Ib/gal (grade 115/145) (lb)... Payload (outbound) (lb)... Payload (inbound) (lb) ... Wing loading (lb/sq ft) ... Stall speed (power off) (kn)... Takeoff ground run at SLi/ (ft)... Takeoff to clear 50 ft 1/ (ft) • • • Rate of climb at SL 2/ (fpm)... Rate of climb at SL (one engine out) (fpm)... Time: SL to 10,000 ft 2/ (min) ... Time: SL to 20,000 ft 2/ (min) Service ceiling (100 fpm) 2/ (ft) • •. Service ceiling (one engine out) 2/ (ft)...

COMBAT RANGE (nmi) ... Average cruising speed (kn)... Cruising altitude (ft)... Total mission time (hr) ...

COMBAT RADIUS 3/ (nmi)... Average cruising speed (kn) ... Cruising altitude (ft) ... Total mission time (hr) ...

FIRST LANDING WEIGHT 3/ (lb) ... Ground roll at SL (ft)... Total from 50 ft .. (ft)

COMBAT WEIGHT 2/ (lb)... Combat altitude (ft) ... Combat speedJ/ (kn) Combat climb 2/ (fpm) Combat ceiling (500 fpm)2/ (ft)... Service ceiling (100 fpm) 2/ (ft) Service ceiling (one engine out) 2/ (ft) ... Takeoff ground run at SL 1/ (ft) ... Takeoff to clear 50 ft i/ (ft) ... Max rate of climb at Sh2/ (fpm) ... Max speed at 12,000 ft 2/ (kn) #

Basic speed at 5000 ft 2/ (kn) LANDING WEIGHT (lb) ...

Ground roll at SL (ft) Total from 50 ft (ft)

J/Maximum power — 3400 rpm. 2/Normal power — 3200 rpm

7700 4/ 1380 778

None 27.5

72 1320 2200 1304

184 8.1

19.1 27.000

7800 1104

134 10.000

8.38 539 130

10,000 8.35

7054 1280 2025 6276

10,000 203

1685 27,200 32,500 15,550

760 1355 1825 207 193

5643 1065 1665

DESIGN MISSION NORMAL MISSION FERRY RANGE

77004/ 1158 1000 None 27.5

72 1320 2200 1304

184 8.1

19.1 27,100

7800 898 135

10,000 6.67 434 130

10,000 6.83 7119 1310 2075 6138

10,000 203

1735 27,700 32.900 15.900

720 1300 1870 207 193

5632 1060 1660

69224/ 1380 None

24.7 68

1000 1720 1550 310 6.8

15.7 30.000 13,500

1220 127

10.000 9.61

5650 10,000

204 1935

29,800 34,600 17,500

600 1060 2100

208 194

5643 1065 1665

77004/ 1380 778

None 27.5

72 1320 2200 1304

184 8.1

19.1 27,100

7800 883 i/ 171

10,000 5.23 4155/

172 10,000

4.97 7044 1285 2030 6266

10,000 203

1670 27,100 32,400 15,450

760 1360 1820 207 193

5643 1065 1665

1-153

1-81. Loading Performance - Typical Mission, U-8F (Seminole) (CONT).

-2/For RADIUS mission if radius is shown,

includes crew of 1 at 200 lb.

-2/65-percent normal power used for cruise.

Performance Basis:

a. Data source: Contractor’s flight test,

b: Performance is based on powers shown.

FM 101-20

1-82. Performance Notes, U-8F (Seminole).


Warm up, take off, climb on course to 10,000 feet at normal power, cruise out at long range speeds to remote base, land, and discharge passengers and baggage. Without refueling, warm up, take off, climb on course to 10,000 feet at normal power, and return at long range speeds. Range-free allowances are 10 minutes of normal power for warmups and takeoffs, plus fuel for 20 minutes at speeds for long range at sea level, and 5 percent of initial fuel for reserve.


Warm up, take off, climb on course to 10,000 feet at normal power, cruise out at 65-percent power to remote base, land, and discharge passengers and baggage. Without refueling, warm up, take off, climb on course to 10,000 feet at normal power, and return at 65-percent power. Range-free allowances are 10 minutes of normal power for warmups and takeoffs, plus fuel for 20 minutes at speeds for long range at sea level, and 5 percent of initial fuel for reserve.

FORMULA: RANGE MISSIONS I, II, & IV

Warm up, take off, climb on course to 10,000 feet at normal power, and cruise out at long range speeds until all but reserve fuel is consumed. Range-free allowances are 5 minutes of normal power for warmup and takeoff, plus fuel for 20 minutes at speeds for

long range at sea level, and 5 percent of initial fuel for reserve.


Warm up, take off, climb on course to 10,000 feet at normal power, and cruise out at 65-percent power until all but reserve fuel is consumed. Range-free allowances are 5 minutes of normal power for warmup and takeoff, plus fuel for 20 minutes at speeds for long range at sea level, and 5 percent of initial fuel for reserve.


Beech Aerodynamic Report 677, Jackson, P.A., Type Inspection Report No. 50-20, Model 65 (L-23F), Gross Weight 7368 lb.

Beech Aerodynamic Report 678 and Appendixes A, B, C, and D, Hughes, A.C., Preliminary Flight-Test Evaluation L-23F Prototype.

Beech Aerodynamic Report 679, Jackson, P.A., Flight-Test Performance, Model 65 (L-23F), 7368 lb.

Beech Aerodynamic Report 695, Jackson, P.A., Type Inspection Report 65-2, Model 65 (L-23F), 7700 lb.

Beech Aerodynamic Report 732, Ross, H.C., U.S. Army Flight Manual Substantiating Data from Beech Flight Tests (L-23F).

Source: DRSTS-WP

FM 101-20

"“i

P

Figure 1-52. U-10A (Helio-Courier)

1-155

FM101-20

39 FT

a

8 FT U FT 8 IN

9 FT DIMENSIONS

I5FT

8 FT 10 IN

52-

o □ CO 1 FT 8-1/2 IN

FT TO 23

Wing: Span i ¡.. 39 Ft. Incidence J.... ! 3° Dihedral Io

Sweepback (LE) outer panel 25 , percent chord. 0.0° '

Sweepback (LE) ' ¡ outer section i ‘ 100 percent chord 0.0°

Length 30 Ft. 3-1/2 In. Height 8 Ft. 10 In. Tread 9 Ft. Prop gnd . ^

clearance 1 Ft. 8-1/2 In.

Figure 1-53. Principal Dimensions, U-10A (Helio-Courier)

1-156

1-157

• • • • • 1-83. U-10A (Hello Courier) Characteristics.

ENGINE

No. & model (1) GO-480- G1D6

Engine spec No ... .2227B Superch NA Red. gear ratio 0.641 (77:120) Prop mfr Hartzell Blade design No ... .B3Z20-1/

10151C-5

Prop type Hydraulic, constant speed

No. blades 3 Prop dia 8 ft Prop type certificate Nn P-907-10

ENGINE RATINGS

BHP RPM Takeoff 295 3400 Normal 280 2750


AIRFRAME: Commercial Manuals

(Contractor Supported)

ENGINE:


Mfr’s Model: Helio-Courier

Basic mission assignments of the U-10A aircraft include courier, observation, cargo carrying, parachute delivery and small groups, radio jfelay for extended periods of time, evacuation, and utility transport.

The U-10A is a versatile air vehicle in the STOL category specifically designed to utilize small, rough, and unprepared fields and offering a maximum of protection for pilot and crew. Adaptability to floats and skis enables the airplane to operate on water and snow.

The U-10A is an all-metal, high-wing, conventional-geared, four- place aircraft. The aerodynamic characteristics feature such items as long-span, high-lift type slotted flaps, and full-span leading edge slots. Lateral control is obtained by short-span, Frise-type, balanced ailerons which are operated in conjunction with leading edge spoilers. Ailerons alone are used for lateral control at higher speed. The airplane has an all-movable, slab-type, horizontal stabilizer with antibalance tab and a large vertical stabilizer and rudder.

The U-10A is powered by a six-cylinder engine splined to a three- bladed propeller with a constant-speed control and spinner to aid engine cooling.

FEATURES PERSONNEL

Adaptable to floats & skis Crew.(normal) (pilot, STOL type aircraft copilot)

Passengers 2 2

WEIGHTS

Empty Max takeoff (normal) . Max takeoff (overload)

LB 2249 3000 3920

FUEL AND OIL

Fuel: Grade 115/145 Spec MIL-G-5572 No. tanks: Wing, left (1) 30 gal Wing, right (1) 30 gal Qty 60 gal

Oil: Spec Temps above +30°F MIL-L-22851 Type II

Temps below +30°F MIL-L-22851 Type III

No. tanks 1 Location Engine sump Qty 2-1/2 gal

AVIONICS/ARMAMENT

Refer to chapter 2.

Commercial Manual FLYAWAY COSTS/NSN

NSN 1510-00964-9780 LIN A 30971 COSTS, $55,824

FM 101-20

FM 101-20

1-84. Loadingand Performanca • Typical Mission, U-1 OA (Helio Courier).

CONDITIONS

Max speed at SL

Max speed, 5000 ft

Min speed, power off, 40-deg flaps

Performance cruise at 6000 ft, 74-percent power, 2750 rpm

Range at 139 kn :

Extended range cruise at 10,000 ft, 49-percent power, 2200 rpm

Range at 121 kn

Max endurance at 5000 ft, 29-percent power, 75 in TAS

Service ceiling (100 fpm R/C)

Takeoff data at SL, 0 wing, 25-deg flaps, paved runway : Takeoff weight

Ground roll

Total distance over 50-ft obstacle

Landing data at SL, 0 wind, 40-deg flaps, paved runway: Ground roll

Total distance over 50-ft obstacle

BASIC MISSION

(kn).

(kn) .

(kn) .

(kn) .

(nmi).

(kn).

(nmi) .

(hr).

(ft).

(lb).

(ft).

(ft).

(ft).

(ft).

145

142

42

139 .

436 (no reserve)

121 ■' '

700 (no reserve)

9.14 (no reserve)

22,000

3000

290

500

180

495

Source: DRSTS-WP

1-158

FMI 01-20

ï»i

Figure 1-54. U-21 and RU-21 (Ute) (paint scheme differences)

1-159

FM 101-20

45 FT 10-1/2 IN

7 FT 9 IN

DIMENSIONS 12 FT 9 IN.

Wing ' ' V Span 45 F^jÄjQ-1/2 In. Incidence s ''

(root) 1..J.. !... 4.8° (tip) HMM ... 0.0°

Dihedral ImR 7° Sweepback (LE) V 0.0° Sweepforward (TE) NVAL

Length 35 Ft. 6 In. Height 14 Ft. 2-1/2 In. Tread 12 Ft. 9 In. Prop gnd

clearance 1 Ft.

17 FT 2-23/32 IN

n r\

35 FT à IN

□ □□ cs

-£

14 FT 2-9/16 IN.

2 DEG

• 12 FT 3-15/32 IN

Figure 1-55. Principal Dimensions, U-21A, U-21G, (Ute)

1-160

FM 101-20

17’ 2.72’

\

N

> i

1i

50’ 10.5

-12’ 9”

35’ 6”

FS30 FS49

FS 160

Ci

losg’^’ 12”

14’ 2.56’’

AV 111172 -12' 3.47

Figure 1-56. Three View Drawing and Dimensions (RU-21A)

1-161

1-162 1-85. U-21A ¡and RU-21A (UTE) Characteristics.

ENGINE

No. & model .... (2) T74-CP-700 (PT6A-20)

Mfr UACL Type Turboprop Prop mfr Hartzell Prop type Hyd, CS, FF No. blades 3 Propdia 7ft.9in.

ENGINE RATINGS

Takeoff SHP 550 ALT SL


AIRFRAME: TM55-1500-340-PMS TM55-1510-209-10 TM55-1510-209-10-1 TM55-1510-209-CL TM55-1510-209-CL-1 TM55-1510-209-23-1&2 TM55-1510-209-23P-1&2 TM-1-U21-S


Mfr’s Model: Beech Aircraft Corporation 65-A90-1

The U-21 A is an off-the-shelf utility aircraft. The first production aircraft was tested by USATECOM for confirmation.

The U-21 A is an unpressurized, low wing, all-metal construction aircraft of versatile design with an all-weather capability. The primary mission of the U-21 A is to perform utility services in the combat zone, support commanders and their staff in command and control, adminstration, liaison and aeromedical evacuation. The basic version of the aircraft is confígured for troop transport; however, alternate configurations are available for service as air ambulance, staff transport, or air cargo transport.

DEVELOPMENT

Date of contract 30 September 1966 Contracting agency AVSCOM No. of test aircraft 3 First flight (scheduled) March 1967 . Completion of test and evaluation July 1967 Contract delivery schedule 2 April 1967

23 May 1967 23 June 1967

WEIGHTS

LB Empty 5401 Gross takeoff 9650 Gross landing 9168 Cargo capacity 3000

FUEL AND OIL

Fuel: Grade Spec No. tanks ... Location ... Qty Location ... Qty

Oil: Spec Temps above -40° F

Temps below -40° F

No. tanks . .. Location ...

JP4/5 MIL-T-5624 10 (8) wing 256 gal (2) Nacelle 114 gal

MIL-L-23699

MIL-L-7808 2 Nacelle ''

ENGINE TM55-2840-232-23P TM55-2840-232-24 TM55-2840-120 (DMWR)

FEATURES

Cabin heating and ventilating system.

Deicing and anti-icing system. Rotating beacon light. Steerable nose wheel. Controllable pitch, full

feathering, and reversible props.

PERSONNEL Pilot

1/Passengérs

^/Troops or

Litter patients plus

Ambulatory patients plus

Attendant

1 6

10

3

3

1

Qty 2.3 gal each tank

AVIONICS/ARM AMENT

Refer to chapter 2.

FLYAWAY COSTS/NSN

U-21A NSN 1510-00933-8223 LIN A30946 COSTS, $348,844

i/ Normal seats •2/Combat - equipped RU-21 À Pilot

' Co-Pilot Equip. Operators

Note:

RU-21 A NSN 151000587-3375

LIN‘A3ft582 COSTS7-

$587,004‘'

RU-21 A: U-21 A Modified for installation of special mission EW equipment.

FM

101-20

1-163 ~\J

1 -86. RU-21D (UTE) Characteristics.

ENGINE MISSION AND DESCRIPTION . i/i v snyvT- 3JS.

No. & model (2) T74-CP-700 (PT6A-20)

Mfr UACL Type Turboprop Prop mfr Hartzell Prop type Hyd,CS,FF No. blades 3 Propdia 7 ft. 9 in.

ENGINE RATINGS

Mfr’s Model: Beech Aircraft Corporation 65-A90-1

The RU-21D is a U-21A aircraft modified to carry special mission equipment.

The RU-21D is a unpressurized, low wing, all-metal construction aircraft of versatile design with an all-weather capability. The primary mission of the RU-21D is to perform special missions in the'combat zone.

DEVELOPMENT



AIRFRAME: TM55-1510-209-10-1 TM-55-1510-209-23-1 TM-55-1510-209-23-2 TM-55-1510-209-23P-1 TM-55-1510-209-23P-2 TM55-1500-209-CL-1 TM 55-1500-34-PM S TM-1-U21-S

ENGINE: TM-55-2480-232-23P TM-55-2480-232-24 DM WR-55-2840-120

Date of contract Contracting agency No. of test aircraft First flight (scheduled) Completion of test and evaluation Contract delivery schedule

RU-21D 2 FEB 68 AVSCOM

MAY 68

JUL 68 OCT 68

FEATURES


Deicing and anti-icing system. Rotating beacon light. Steerable nose wheel. Controllable pitch, fulj


PERSONNEL

Pilot Co-Pilot Equipment Operators

LB Empty (wet) 6497 Gross takeoff 9650 Gross landing 9168 Cargo capacity 3000

FUEL AND OIL

Fuel: Grade JP4/5 Spec MIL-T-5624 No. tanks .10 Location' (8) wing Qty 256 gal Location (2) Nacelle Qty 114 gal

Oil: Spec . Temps above 40OF MIL-L-23699 Temps below 40op MIL-L-7808

No. tanks 2 Location Nacelle Qty 2.3 gal each

tank

AVIONICS/ARM AMENT

Refer to chapter 2.

FLYAWAY COSTS/NSN

NSN 1500-00804-3641 LIN A30585 COSTS $875,004

FM 101-20

FM 101-20

1-87. Performance - Typical Mission, U-21A(UTE).

Payload

Range

Cruise speed 2^

Max speed

Min takeoff distance . . .

Min landing distance . . .

Rate of climb ( 1 engine).

Service ceiling (2 engines)

Service ceiling (1 engine) .

2000 J/ (lb)

(nmi) 1249

(kn) 180

(kn) 230

ft) 1000

(ft) 800

(fpm) 350

(ft) 25,000

ft) 10,000

-^3000 lb with fuel trade off.

•2/ True airspeed at normal rated power.

Source: DRSTS-WP

1-164

FM 101-20

17FT 2.7181 N

\ r\

n

45FT 10.500IN

C >

7FT9IN

OP

1FT 6 N 10.500IN 12FT 9IN

35FT6IN—

FS 30

FS 160 FS 49

J2

□ I. O 14FT 2.562IN

Io 39MIN 12SEC O 12IN

12FT 3.468IN

Figure 1-57. Principal Dimensions Diagram RU-21D 1-165

FM 101-20

1-88. Performance - Typical Mission, RU-21D(UTE).

Payload

Range

Cruise speed JL^

Max speed

Min takeoff distance ....

Min landing distance ....

Rate of climb (1 engine) .



• -Ob)

(nmi)

. (kn)

. (kn)

. .(ft)

...(ft)

• (fpm) ...(ft)

. . .(ft)

l,767Jy

800

176

230

1,700

1,280

410

25,750

9,100

^/Mission equipment and two operators.

-2/True airspeed at normal rated power.


1-166

FM 101-20

7.45 IN

Qi

□ W

DIMENSIONS

22 FT 4.6 IN K-|

Wing: Span 45 Ft. 10.5 In. Incidence

(root) 4.8° (tip) 1.0°

Dihedral '. 7° Sweepback (LE) 0.0° Sweepforward (TE) NVAL

Length 39 Ft. 11.36 In. Height 15 Ft. 4.25 In. Tread 13 Ft. Prop gnd

cléarance I Ft. 1 In.

45 FT 10.5 IN

7 FT6 IN DIA.

Pi

13 FT

39 FT 11.36 IN

2)0 ioj o o o o o 15 FT 4.25 IN

((pj 13.50 IN JO

1-14 FT 11 IN Ji

Figure 1-56. Principal Dimensions U-21F (Ute) 1,167

1-168

1-89. U-21F (UTE) Characteristics.


No. & model (2) PT6A-28 Mfr UACL Type Turboprop Prop mfr Hartzell Prop type Hyd, CS, FF No. blades 4 Prop dia 7 ft. 6 in.

ENGINE RATINGS

Mfr’s Model: Beech Aircraft Corporation A100

The U-21F is an off-the-shelf utility aircraft.

The U-2 IF is a pressurized, low wing, all-metal construction aircraft of versatile design with an all-weather capability. The primary mission of the U-21F is to transport high ranking military and government officials.

Takeoff SHP 680 ALT SL DEVELOPMENT



Date of contract 30JUN71 Contracting agency AVSCOM No. of test aircraft — First flight (scheduled) MAY 71 Completion of test and evaluation - Contract delivery schedule 30 JUL 71

30 AUG 71

FEATURES


Deicing and anti-icing system. Rotating beacon light. Steerable nose wheel. Controllable pitch, full


Pressurized cabin. Air conditioning.

PERSONNEL

Pilot Co-Pilot .. Passengers

LB Empty (wet) 6790 Gross takeoff 11,500 Gross landing 11,210

FUEL AND OIL

Fuel: Grade JP4/5 Spec MIL-T-5624 No. tanks 14 Location 10 wing Qty 274 gal Location (2) Nacelle Qty 114 gal Location (2) Center

Section Qty 82 gal

Oil: Spec Temps above 40°F MIL-L-23699

Temps below 40°F MILL-7808

No. tanks 2 Location Nacelle Qty 2.3 gal each

tank

AVIONICS/ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS/NSN i

NSN 1510-00169-0295 LIN A30951 COSTS $494.800

FM 101-20

FM 101-20

1-90. Performance - Typical Mission, U-21F(UTE).

Payload

Range

Cruise speed .2/

Max speed

Min takeoff distance ....

Min landing distance ....

Rate of climb (1 engine) .



. . .(lb)

. (nmi)

. (kn)

. (kn)

...(ft)

..(ft)

(fpm)

..(ft)

..(ft)

1,4001/

1,000

236

270

1,855

866

452

24,850

9,300

-1/3000 lb with fuel trade off.


Source: DRSTS-WP

i

i

1-169

FM 101-20

17 FT 2-23/32 IN

r\

DIMENSIONS

Wing ■> S Span d5:Ftvl;0-l/2 In.. Incidence

(root) 4.8° (tip) 0.0°

Dihedral 7° Sweepback (LE) 0.0° Sweepforward (TE) NVAL Length 35 Ft. 6 In. Height 14 Ft. 2-1/2 In. Tread T2Ft. 9In. Prop gnd

clearance 1 Ft.

45 FT .10-1/2 IN

7FT9IN

12 FT9 IN

-i-12 FT 3-15/32 IN ——|

14 FT 2-9/16 IN

35 FT 6 IN

FS 30

FS 49 FS 160

UL

a ! I

12 IN M N

Figure 1- 57. Principal Dimensions RU-21B and RU-21C (Ute)

1-170

1-171

fRU-2 RU-21C (UTE) Characteristics.

ENGINE

No. & model (2) T74-CP-702 (PT6A-29)

Mfr UACL Type Turboprop Prop mfr Hartzell Prop type Hyd, CS, FF No. blades 3 Prop dia 7 ft. 9 in.

ENGINE RATINGS

Takeoff SHP 620 . ALT SL


AIRFRAME: TM55-1500-34Ö-PMS TM-55-1510-214-10 ' TM-55-1510-214-CL TM-55-1510-214-23 ; TM-55-1510-209-23P 1&2 TM-1-U21-S

ENGINE: TM-55-2840-232-24 TM-55-2840-232-23P


Mfr’s Model: Beech Aircraft 65-A90-2 (RU-21B) 65-A90-3 (RU-21C)

The RU-21 B & C models are modified U-21A to carry special ASA mission equipment. They have engines with greater SHP, are beefed up to accomodate higher gross weight, and are equipped with dual wheel landing gears.

DEVELOPMENT

Date of contract, Amendment 12 Jun 1967 Contracting agency AVSCOM No. of test aircraft 2 First Flight (Scheduled) Aug 1968 Completion of Test and Evaluation Final test

' - not completed Contract Delivery Schedule (Est Apr 72)

FEATURES

Cabin heating and ventilating system. Deicing and anti-icing system. Rotating beacon light. Steerable nose wheel. Controllable pitch, full feathering, and reversible props.

PERSONNEL

Pilot 1 Copilot .1 Mission Equipment Operator

RU-21B 3 RU-21C 2

Passengers 0

WEIGHTS

LB Empty .. RU-21B 5955

: . RU-21C 5907 Gross takeoff 10,900 Gross landing 10,900

FUEL AND OIL

Fuel: Grade Spec ,

JP4/5 MIL-T-5624

B MODEL No. Tanks Location . Qty Location . Otv

12 (10) Wing 290 gals (2)Nacelle 106 gals

C MODEL No. Tanks Location . Qty Location . Qty .... .-

OU: Spec

Below ..

Above ..

No. tanks Location . Qty

12 (8) wing 290 gals (2) Nacelle 106 gals

40oF(25°Q . MIL-L-7808 40°F(25oC) MIL-L-23699 2 Nacelle 2.3 gal each tank

AVIONICS/ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS/NSN

RU-21B NSN 1510-00878-4338 LIN A30583 COSTS $1,257,811

RU-21C NSN 1510-00878-4336 LIN A30584 COSTS $1,259,760

FM

101-20

FM 101-20

1-92. Performance - Typical Mission, RU-21B/RU-21C(UTE).

Payload (lb)

Range (nmi)

Cruise speed (kn)

Max speed (kn)

Min takeoff distance (ft)

Min takeoff distance (ft)

Min landing distance (ft)

Min landing distance (ft)

Rate of climb (1 engine) (fpm)

Rate of climb (1 engine) (fpm)

Service ceiling (2 engines) (ft)

Service ceiling (1 engine) (ft)

1371 16S8

940 940

194

208

2860

2140

1750

1360

208

365

20,000

7,000

V J/

-^Mission Equipment


B Model C Model

B Model C Model

B Model

C Model

B Model

C Model

B Model

C Model

1-172

FM 101-20

17 FT 2.72 IN

CD

DIMENSIONS

Wing Span 50 Ft. 11 In.

Incidence (root) 4.8° (tip) 0.0°

Dihedral 7° Sweepback(LE) 0.0° Sweepforward

(TE) NVAL Length 35 Ft. 26 In. Height 14 Ft. 2-1/2 In. Tread 12 Ft. 9 In. Prop gnd

clearance . 1 Ft.

50FT11 IN.-

FT IN

o &

12FT9IN.

35 FT 6 IN

a a o 14 FT 2.56 IN

i ILL12 IN

1° 39 FT 12 IN.

12 FT 3.47 IN.

Figure 1-58. Principal Dimensions RU-21H (Guardrail V)

1-173

1-174

1-93. RU-21H (Guardrail V) Characteristics.


No. & model .... (2) T74-CP-700 (PT6A-20)

Mfr UACL Type Turboprop Prop mfr Hartzell Prop type Hyd, CS, FF No. blades 3 Prop dia 7 ft. 9 in.

ENGINE RATINGS

The RU-21H is an unpressurized, all meted low wing aircraft powered by two T74-CP-700 turboprop engines. Distinguish- able features of the acft are the slender, streamline engine nacelles, square-tipped tail services, and swept back vertical stabilizer with ventral fin. Vertically oriented antennas and tip pods are installed on the wings. Cabin entrance and egress is made through an air-stair type door on the left side of the fuselage. An escape hatch is also fitted in the top of the pilots compartment. The primary missions of this acft are signal intelli- gence and electronic surv. Features include IR paint scheme.


TECHNICAL PUBLICATIONS DEVELOPMENT

AIRFRAME: TM-1-U21-S

TM-55-1510-215-10-2 TM-55-1510-215-CL-2 TM-55-1510-215-23-1 TM-55-1510-215-23-2 TM-55-1510-209-23P1&2 TM-55-1510-215-PMS TM-55-1500-340-PMS

Date of contract Contracting agency No. of test aircraft First flight (scheduled) Completion of test and evaluation Contract delivery schedule

FEATURES

Cabin heating and ventilating system.

Deicing and anti-icing system.

Rotating beacon light. Steerable nose wheel. Controllable pitch, full


Capacitance Fuel Gaging System

Pilot .. CoPilot

30JUN 76 .USACERCOM PIP N/A SEP 78 SEP 78 -FEB 80

PERSONNEL

1 1

WEIGHTS

LBS. Basic 6480 Gross takeoff 10,200 Gross landing 9700 Mission Equip 1000

FUEL AND OIL Fuel:

Grade JP4/5 Spec MIL-T-5624 No. tanks 10 Location (8) wing Qty 256 gal Location (2) Nacelle Qty 114 gal

Oil: Spec Temps above 32°F MIL-L-23699 Temps below 32°F MIL-L-7808 No. tanks 2 Location Nacelle Qty 2.3 gal each tank

AVIONICS/ARM AMENT

Refer to chapter 2.

FLYAWAY COSTS/NSN

NSN 1510-00-3943320 COSTS $1,501,200.00 LIN Z04570

© x

cp

FM 101-20

FM 101-20

1-94. Performance - Typical Mission, RU-21H (UTE)

Payload ■.. . .(lb)

Range (nmi)

Cruise speed .2/ (kn)

Max speed (kn)

Min takeoffdistance (ft)

Min landing distance .(ft)

Rate of climb (I engine) (fpm)

Service ceiling(2 engines) .(ft)

Service ceiling (I engine) (ft)

1,767 U

800

176

230

1,700

1,280

410

25,750

9,100

JL/ Mission equipment and two operators.


Source: DRCPM-AEL(2)

1 I

1-175

FM 101-20

15 FT 0 IN.

43 FT 9 IN.

D OOOOO O aa>

14.5 IN. O

15 FT

29.6 IN.

Ó

DIMENSIONS

Wing Span 54 Ft. 6 In. Length 43 Ft. 9 In. Height 15 Ft. 0 In. Tread 17 Ft. 2 In.

Prod Grd Clearance... 1 Ft.

■ 18 FT 5IN.-

54 FT. 6 IN. -Ô-

8FT. 2.5 IN. DIA

17FT2IN.

1-176 Figure 1-61. RU-21J

1-177

1-95. RU-21 j Characteristics


No. and Model (2) PT6A-41 Mfr UACL Type .. Turbo Prop Prop Mfg Hartzell Prop Type C5 No. Blades 3 Prop Dià 8 ft. 2*/» in.

ENGINE RATINGS

TAKEOFF SHP 850 ALT SL

Mfg. Model: Beech Aircraft Corp A100-1

The RU-21J an off-the-shelf utility aircraft which is totally contractor supported.

The Ru-21 J is an aU metal twin turbo prop engine, fixed wing, pressurized cabin, passenger/cargo carrying aircraft. The aircraft is designed and equipped for flight operations under Instrument Flight Rule (IFR) conditions day or night into high density air traffic control zones and into known icing weather conditions. The primary mission of this aircraft is to carry special electronic mission equipment in support of development programs.

DEVELOPMENT

Date of contract First flight (Similar aircraft) First acft delivered

1971 N/A July 1974

TECHNICAL PUBLICATIONS FEATURES

AIRFRAME:


ENGINE:

All Metal T-Tail Retractable Tricycle with

Dual Main Wheel Duel Side by Side Flight Controls

PERSONNEL

Crew 2 Passengers N/A

LOADING Empty Basic Design Combat


Max. Takeoff Max. Landing

-LB.

FUEL AND OIL

Fuel: Grade JP 4/5 Spec MIL-T-5624 No. tanks 12 Location 10 Wing

2 Nacelle Qty 1... 386 (544 w/

Aux Tanks) OU:

Spec MIL-L-23699 No. tanks 2 Location Nacelle Qty....... 3.5 Gal Each Tank

AVIONICS / ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS / NSN

NSN 1520-00124-0914 LIN Z04615 $1,817,888

FM 101-20

FM 101*20

1-96. Performance — Typical Mission, RU-21J

Payload (LB) Range (NMI) Cruise Speed (KN) Max Speed (KN) Min Takeoff Distance (FT) Min Landing Distance (FT) Rate of Climb (1 Eng) (PPM) Service Ceiling (2 Eng) (Ft) Service Ceiling (1 Eng) (Ft)

Source: TSARCOM: DRCPM-AEL

1*178

FtMl 101 ■20

Figure 1-62. UV-18A (Twin Otter)

1-179

FM 101-20

20 FT-8 IN.

~T 57.00

CHORD _t

CABIN VOLUME (USEABLE) BAGGABE COMPT-VOLUME-REAR BAGGAGE COMPT-VOLUME-REAR

(MOD 6/1075) BAGGAGE COMPT-VOLUME-FWD

384 CU FT 52 CU FT 88 CU FT

22 CUFT

DIMENSIONS

Wing Span .. .65 Ft. 0 In. Incidence

(root) 2!/2° (tip)

Dihedral 3° Sweepback (LE) Sweepback (TE).. Length 51 Ft. 9 In. Height 19 Ft. 6 In. Tread 12 Ft. 2 In.

~f 78.00

CHORD

_L_ 2 -O.

5 FT-3.75 IN.

L_

18 FT-2.24 IN.

fff

W

■65 FT 0 IN. SPAN

CLEARANCE-Ä-

■ 25'6^ 111 110.00—«-(

®¡B f 3° DIHEDRAL

*9 FT-3 IN.

GROUND LINE

*11 FT-4IN

h *12 FT-2 IN.—-

1-180 Figure 1-63. Principal Dimensions

UV-18A (Twin Otter)

1-97. UV-18A Characteristics.

ENGINE

No. and Model (2) PT6A-27 Mfr Canadian P&W Engine Spec. No 583 Prop mfg Hartzell Prop type C5 No: blades 3

ENGINE RATINGS

SHP Take-off 620 Max Cruise 620

Condition ISA+18°C ISA+6°C


AIRFRAME:


ENGINE:

Commercial Manual


The aircraft with a crew of two is capable of carrying twenty passengers with baggage in the utility seating arrangement to provide command . administrative, logistics and personnel flights from battalion headquarters to remote sites throughout western and northern Alaska on a year-round basis. With the utility seats folded a partial or full freight-carrying configuration is available. With necessary adaptations, the aircraft may be used in an air ambulance, rescue, forrestry / pipeline patrol and air drops of personnel equipment and supplies missions.

DEVELOPMENT

Date of contract First flight (Similar aircraft) First acft delivered Dec 1976

FEATURES

All metal, high wing monoplane

Fixed tricycle landing gear

Conventional three control, dual side-by-side rudder pedal / control column combination

PERSONNEL

Crew Passengers

.2 20

WEIGHTS

LOADING LB. Empty Basic Design Combat


Max. Takeoff 12,500 Max. Landing 12,300

(C) Calculated ♦For Basic Mission

FUEL AND OIL

Fuel: Grade JP4/5 Spec MIL-J-5624G No. tanks 10 Lociîon 8 under floor. ^ 2 in Wing

Qty 2745 Lbs. OU:

Spec MIL-L-23699 No. tanks 2 Location in Engines Qty

AVIONICS/ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS/NSN

NSN 1510-01011-1462 LIN A30989 COSTS $714,945

os

FM 101-20

1-98. Performance — Typical Mission, UV-18A (Twin Otter).

Payload .(LB) Range (NMI) Cruise Speed (KN) Max Speed (KN) Min Takeoff Distance (FT) Min Landing Distance (FT) Rate of Climb (1 Engine) (FPM) Service Ceiling (2 Engines) (FT) Service Ceiling (1 Engine) (FT)

J/4083 Lb with fuel trade off.

30031/ 400 181

1200 1050 340

26,700 11,600

Source: DRSTS-WP

FM 101-20

# CHAPTER 2

LOGISTICSAND MATERIAL

Section I. MAXIMUM ALLOWABLE OPERATING TIME (MAOT) (MAJOR COMPONENTS)

2-1. Major Components.

This section was eliminated since the applicable Technical Manuals (TM’s) are now included in Chapter 1, Section IV, Standard Aircraft Charac- teristics. The TM is more current and in more detail than FM 101-20. Refer to the characteristics pages of each individual aircraft in Section IV. The -20, Chapter 3 of the applicable TM lists all Maximum Allowable Operating Time (MAOT) and Time Between Overhaul (TBO).

#

2-1

FM 101-20

Section II. AIRCRAFT EQUIPMENT

2-2. Avionics and Surveillance Equipment Con- figurations.*

The following avionics and surveillance configurations are typical and may vary depending on production run, changes incorporated through MWO action, and theater of operation in which the

aircraft is employed. For further details on Army Aircraft configuration, including retrofit objectives, refer to AR 95-71 U.S. Army Avionics or TB43- 0123. CERCOM does not maintain configuration information for aircraft which are type classified contingency (U-l, U-6, U-9 etc.).

♦Source: CERCOM (DRSEL-MME-LAE) AND (DRSEL-LE-EA)

The following configuration depicts a typically configured AH-1 ( ). The actual configuration may vary depending on peculiar geographic requirements or changes incorporated through MWO action and special purpose alterations.

N to

cq 0> o CO cs

TYPE NUMBER

AH-1

FUNCTION / NOUN

O « H O SC <

Q O s m SC <

o BS SC t-

>- CO

SC <

S3 B¡ SC E-

GO

SC <

D BS SC E- n o> o CO O)

X <

AM-3209/ASN Servoamplifier

AN/AAS-32 Airborne Laser Tracker

AN/ALQ-144 Countermeasures Set CPO

AN/APN-209 (V) 1 Radar Altimeter

AN/APR-39 (V) 1 Radar Warning Set CPO CPO CPO

AN/APX-72 IFF Transponder

AN/ARC-51BX UHF-AM Radio Set

AN/ARC-54/131 VHF-FM Radio Set

AN/ARC-114A VHF-FM Radio Set

AN/ARC-115 A VHF-AM Radio Set

AN/ARC-116 UHF-AM Radio Set

AN/ARC-134 VHF-AM Radio Set

2-2

FM 101-20

2-2. Avionics and Surveillance Equipment Configuration (Cont).

TYPE NUMBER

AN/ARN-83

AN/ARN-89B

AN/ARN-123(V)3

AN/ASN-43

AN/ASN-128

AS-1304/ARN

AS-2285/ARC

AS-3188/ARN

(214-077-092-1)

AS-3204/ARC

(209-075-550)

AS-3205/ARC

(205-075-345-3)

AT-256AyARC

AT-640/ARN

AT-741/A

AT-884/APX

AT-1108/ARC

AH-1

FUNCTION / NOUN

ADF Set

ADF Set

VOR/MB/GS Set

Gyro Compass Set

Doppler Nav Set

VOR Antenna

FM Comm Antenna

GS Antenna

VHF-AM Antenna

FM Homing Antenna

UHF Antenna

MB Antenna

IFF Antenna

IFF Antenna

VHF AM/UHF Antenna

O rH

X H

O

X <

Q O s

X <

X ai * H <o

>* 6t.

X <

4 CPO

CT! O «

D « X

X <

D ot X E- co

X <

CPO 4 CPO

2-3

FM 101-20

2-2. Avionics and Surveillance Equipment Configurations (Cont).

TYPE NUMBER

AH-1

FUNCTION/NOUN

X H O K <

Q O

CO

X <

D Bi X E- co

>H

CO

X <

D a x EH

X <

D « x EH

CO

X <

BB-649/A Battery

C-1611/AIC Intercomm Set

C-6347/ASN-43 Compass Control

C-6533/ARC Intercomm Set

C-8157/ARC Control-Indicator

C-10533/APX-100 Control

CN-1314/A Gyro

CN-1497/A Gyro

ID-48/ARN Course Indicator

ID-250/ARN RMI

ID-998/ASN

ID-2103/A

RMI

(209-075-660) Horiz Situation Indicator

ID-2104/A

(209-075-661) Attitude Dir Indicator

ID-2105/A

(212-070-180) RMI

KIT-1A/TSEC IFF Computer CPO CPO CPO CPO CPO

2-4

FM 101-20


TYPE NUMBER

AH-1

FUNCTION / NOUN

O o s co

3 oe x t- «

CO

as <

0> o n

D

a fr-

eo

a <

3 oi

o « Csi

co

à <

MC-l Switch Rate Gyro

MD-736/A Signal Discriminator

MT-3513/APX Mount (TS-1843)

MT-3802/ARC Mount (KY-28)

MT-3949A/U Mount (KIT-1A)

MT-4811/APX-100 Mount (RT-1157)

PP-6508/U Static Inverter

PP-7274/A Static Inverter

PU-543/A Inverter

RT-1157/APX-100(V) IFF Transponder

RT-1167/ARC-164 UHF-AM Radio Set

TRU-2A/A Turn Rate Gyro

TS-1843/APX IFF Test Set

TSEC/KY-28 Comm Security Set CPO CPO CPO CPO CPO

206-075-597-1 Audio Threshold System

209-030-133-3 ADF Sense Antenna

209-075-292-1 FM Homing Antenna

209-077-203 FM Comm Antenna

2-5

FM 101-20


AH-1

TYPE NUMBER FUNCTION/NOUN

O X E"

X <

Q O s

x E- (0

ÎH Es«

X <

01 0> o «

D « S H C*3 CO

CO ± <

D 02 X H eo 0) O eo 04

X <

570A SCAS

YG 1054D1 Prox Warning System

NOTES:

1. CPO in FY 76 aircraft.

2. The AN/ARC-116 was installed in lieu of the RT-1167/ARC-164 in a few early FY 76 aircraft.

3. Due to vibration requirements, only the MT-3791C/ARC-134 should be installed as a part of the AN/ARC -134 system.

4. Equipment to be 100% installed in Europe.

5. Equipment installed only in aircraft located at Ft. Bragg, Ft. Campbell, Ft. Hood and Ft. Rucker.

GENERAL NOTES: Configurations shown for all FY 77 aircraft were proposed only, not firm, at the time of this printing.

Present plans call for the conversion of all AH-1 ( ) aircraft to the 77-23093 thru 77-23125 configuration by FY 84.

APPLICABLE AIRCRAFT AVIONICS MANUALS:

TM 11-1520-221 Series (Pertains to AH-1G, S (MOD) TM 11-1520-236 Series (Pertains to AH-1S)

2-6

FM 101-20

2-2. Avionics and Surveillance Equipment Configuration (Cont).

The following configuration depicts a typically configured CH-47( ). The actual configuration may vary depending on peculiar geographic requirements or changes incorporated through MWO action and special purpose alterations.

CH-47

to >* b.

o cc

¡3 Pi X E" (N

3

E E- t- oo o

TYPE NUMBER FUNCTION/NOUN ■É o

X o

X u

X u

■ X o

X Ü


AN/APN-209(V)2 Radar Altimeter

AN/APR-39(V)1 Radar Warning Set CPO CPO



AN/ARA-31 FM Antenna Group

AN/ARC-44 VHF-FM Radio Set


AN/ARC-54/131 VHF-FM Radio Set . 1


AN/ARC-73 VHF-AM Radio Set CPO CPO CPO CPO

2-7

FM 101-20


TYPE NUMBER

CH-47

FUNCTION/NOUN

D

X Cl <0

>- fc.

SB a

<» o a>

P at X fr-

ei

CO CO

SB Ü

«

SB O

O c* TP

X Ü

s o

AN/ARC-102 HF-AM Radio Set CPO CPO CPO CPO CPO CPO




AN/ARN-30E VOR Set

AN/ARN-59 ADF Set

AN/ARN-82 VOR Set

AN/ARN-83 ADF Set

AN/ARN-89 ADF Set

AN/ARN-123(V)1 VOR/MB/GS Set

AN/ASN-43 Gyro Compass Set

AS-1304/ARN VOR Antenna

AS-1703/AR FM Comm Antenna

AS-1869/ARN

AS-1870/ARN

AS-1922/ARC

AT-326/ARN

AT-450/ARC

ADF Sense Antenna

ADF Sense Antenna

FM Homing Antenna

GS Antenna

UHF Antenna

2-8

FM 101-20


TYPE NUMBER

AT-640/ARN

AT-740/A

AT-884/APX

CH-47

FUNCTION/NOUN

MB Antenna

IFF Antenna

IFF Antenna

to

>< Ex.

X O

ti to D OS X H to >•

X ü

1 '

D ct a e i> 00 o to to

X O

m tr

X O

X u

s u

AT-1108/ARC VHF-AM/UHF Antenna

BB-432/A Battery


C-4209/ARC Control (T-366)



CN-811AASN Gyro

CN-1404/ARN-89 Compensator

CU-942B/ARC FM Antenna Coupler

CU-991/AR HF Antenna Coupler CPO CPO CPO CPO 6 CPO

CU-1658/A

CV-1275/ARN

ID-250/ARN

ID-998/ASN

ID-1347C/ARN

HF Antenna Coupler 6CP0 CPO

Converter

RMI

RMI

Course Indicator

2-9

FM 101-20

2-2. Avionics and Surveillance Equipment Configurations (Cent).

TYPE NUMBER

J-2

KIT-1A/TSEC

M-40A

MD-736/ A

•MT-1142/ARC

MT-1719/AR

MT-2292/ARN

MT-2641/ARC

MT-3513/APX

MT-3772/A

MT-3802/ ARC

MT-3949A/U

PP-2792/ARN-30

R-1041/ARN

R-1963/ARN

RT-1167/ARC-164

RT-1285/APX-100

CH-47

FUNCTION/NOUN

Gyro Compass Set

IFF Computer

Mount (CV-1275)

Signal Discriminator

Mount (T-366)

Mount (CU-991)

Mount (R-1041)-

Mount (AN/ARC-102)

Mount (TS-1843)

Mount (CU-1658)

Mount (KY-28)

Mount (KIT-1A)

Power Supply

MB Receiver

MB/GS Receiver

UHF-AM Radio Set

IFF Transponder

CPO

10

CPO

CPO

CPO

10

CPO

a> 0 o> <x> to D 01 a H r- œ o to to

X O

CPO

CPO

10

CPO

CPO

CPO

10

CPO

o t-

X

CPO

6 CPO

10

6 CPO

CPO

CPO

10

CPO

2-10

FM 101-20


TYPE NUMBER

CH-47

FUNCTION/NOUN

CO

>H

X o

co 00 o CO CO

D X X H cs CO

pH

X O

a» o O) <b CO

s ai X

00 o tb to

X o

a

x u

SB Ü

SC Ü

T-366/ARC ■VHF-AM Transmitter


TSEC/KY-28 Comm Security Set CPO CPO CPO CPO CPO

TSEC/KY-58 Comm Security Set aCPO ’CPC

114E2186-( ) Speed Trim Amplifier

114E3030-C ) SAS Amplifier

114E3094-I ) HF Antenna CPO CPO CPO CPO CPO CPO

9000F Gyro

YG1054D1 Proximity Warning System UJ 11J

* 2-11

FM 101-20


NOTES: 1. Proposed retrofit installation. 2. Proposed retrofit replacement for AN/APX-72. 3. The AN/ASN-43 was installed in lieu of J-2 starting with FY 65 aircraft. 4. May be replaced by C-10414/ARC. 5. The SBU-6A and 9000F gyros are acceptable substitutes and may be installed in lieu of the CN-811. 6. Provisions for the CU-1658 and MT-3712 were installed in CH-47C aircraft starting with 68-15835.

Prior aircraft have provisions for the CU-991 and MT-1719. 7. Proposed retrofit replacement for AN/ARC-51. 8. Not required when AN/APX-100 is installed. 9. Proposed retrofit replacement for KY-28.

10. Used in lieu of PP-3702/ARC-102. : . 11. Equipment installed only in aircraft located at Ft. Bragg, Ft. Campbell, Ft. Hood and Ft; Rucker.

GENERAL NOTE: The configuration shown for the CH-47D was proposed only, not firm', at the time of this printing.


TM 11-1520-209 Series.

2-12

FM 101-20


The following configuration depicts a typically configured CH-54 ( ). The actual configuration may vary depending on peculiar geographic requirements or changes incorporated through MWO action and special purpose alterations.

CH-54

TYPE NUMBER FUNCTION/NOUN S o

X o


♦AM-6279/ASW Amplifier

♦AM-6280/ASW Amplifier




AN/ARC-102 HF-AM Radio Set CPO CPO


AN/ARN-82 VOR Set

AN/ARN-83 ADF Set

AN/ASH-19

AN/ASH-23

Voice Warning Set

Voice Warning Recorder

2-13

FM 101-20


CH-54

TYPE NUMBER

AN/ASN-43

FUNCTION/NOUN

Gyro Compass Set

PQ -r

K o

AN/ASW-29 Auto Fit Cont System


AS-1703/AR FM Conun Antenna

AS-1922/ARC FM Homing Antenna

AT-326/ARN

AT-640/ARN

GS Antenna

MB Antenna

AT-884/APX IFF Antenna


BB-434/A Battery

C-1611/AIC

*07266/ASW-29

C-8157/ARC

*C:8476/ASW

»C-8477/ASW

•C-8478/ASW

CN-1314/A

•CN-1325/ASW

Interconun Set

Control

Control-Indicator

Control

Control

Control

Gyro

Gyro

2-14

PM 101-20


TYPE NUMBER

CH-54

FUNCTION/NOUN X o

pa

X o

CU-942/ARC FM Antenna Coupler

CU-991/AR

CU-1658/A

HF Antenna Coupler CPO

HF Antenna Coupler 2CPO CPO

ID-250/ARN RM I

ID-998/ASN RM I

♦ID-1720/ASW Indicator

KIT-1A/TSEC IFF Computer CPO CPO


MT-1719/AR Mount (CU-991) 2CPO


MT-3772/A Mount (CU-1658) 'CPO CPO


MT-3949AyU Mount (KIT-1A)

♦MX-8611/ASW Accelerometer

PU-543/A Inverter

R-1963/ARN MB/GS Receiver CPO CPO

RT-1167/ ARC-164 UHF-AM Radio Set

•SN-410/ASW-29 Synchro

2-15

FM 101-20


CH-54

< -rf lO

m

TYPE NUMBER

•SN-441/ASW

•SN-442/ASW

TS-1843/APX

TSEC/KY-28

6460-65010-041

s FUNCTION/NOUN

Synchronizer

Synchronizer

IFF Test Set

Comm Security Set

ADF Sense Antenna

Ü O

2

2

1 1

CPO CPO

1 1

* Denotes components of Automatic Flight Control System (AFCS) installed on the CH-54B. Some of these items are components of the AN/ASW-29 AFCS installed on the CH-54À.

NOTES:

1. Proposed retrofit installation. 2. Provisions for the CU-991 and MT-1719 were installed in 66-18408 thru 66-18413. All other CH-54A

aircraft have provisions for the CU-1658 and MT-3772. 3. Proposed retrofit replacement for AN/ARC-51.


TM 11-Í520-217 Series

2-16

FM 101-20


The following configuration depicts a typically configured OH-6A. The actual configuration may vary depending on peculiar geographic requirements or changes incorporated through MWO action and special purpose alterations.

OH-6A


CD

>• Cb

to

!H b < to

X o

a> to

>* b* ao to

*

< H» X o




AN/ARC-111 VHF-AM Radio Set CPO

AN/ARC-114 VHF-FM Radio Set #1 1 .

AN/ARC-114 VHF-FM Radio Set »2 3 CPO


AN/ARC-116 UHF-AM Radio Set v AN/ARN-83 ADFSet

AN/ARN-89 ADFSet

AN/ARN-123(V)1 VOR/MB/GS Set lCPO CPO


2-17

FM 101-20


TYPE NUMBER

OH-6A

FUNCTION/NOUN

to >« fa lO <o >< fa < <o X O

os <c >< fa CO CO

> fa < CO

á o

AS-1703/AR #2 FM Comm Antenna

AT-640/ARN MB Antenna


BB-641/A Battery

BB-678/A Battery





CU-1794/ARC 01 FM Homing Xfmr

CU-1796/ARC #1 FM Homing Ntwk

CU-1893/ARC #1 FM Antenna Coupler

CU-1894/ARC 02 FM Antenna Coupler

ID-1347C/ARN Course Indicator

ID-1351/A Heading Indicator

KIT-1 A/TSEC IFF Computer iCPO CPO


MT-3949A/U Mount (KIT-1 A)

2-18

FM 101-20


TYPE NUMBER

OH-6A

FUNCTION/NOUN

fa <o >• fa < u>

X O

fa 00 u>

>- fa < w X O




TSEC/KY-28 Comm Security Set CPO

369A 4554 Static Inverter

369A 6471 Mount (KY-28)

369A6472 Mount (KIT-1A)

ILS-l-MIL VOR/GS Antenna

NOTES:

1. Proposed retrofit installation. 2. The AN/ARC-51 was installed in lieu of the AN/ARC-116 in some aircraft. 3. Wiring provisions exist for 2 each AN/ARC-114, 1 each AN/ARC-115 and 1 each AN/ARC-116. How-

ever, the maximum number of sets that can be installed'at any given time is limited to 3 each, i.e., 1 each AN/ARC-114,115 and 116 or 2 each AN/ARC-114 and’l each AN/ARC-115 or 2 each AN/ARC-114 and 1 each AN/ARC-116.

4. The PP-6376 is a proposed retrofit replacement for the PP-6674 and 369A 4554 inverters.


TM 11-1520-214 Series

2-19

FM 101-20


The following configuration depicts a typically configured OH-58 ( ). The actual configuration may vary depending on peculiar geographic requirements or changes incorporated through MWO action and special purpose alterations.

OH-58


< 00 ta

X o

CJ oo m S o


AN/APR-39(V)1 Radar Warning Set CPO



AN/ARC-114 VHF-FM Radio Set #1

AN/ARC-114 VHF-FM Radio Set #2 CPO CPO



AN/ARN-89 ADF Set

AN/ARN-123(V)1 VOR/MB/GS Set !CPO



2-20

FM 101-20


TYPE NUMBER

OH-58

FUNCTION/NOUN X o

Ü oo

X O

AS-2485/ARC

(206-075-543-1) #2 FM Comm Antenna

AS-2486/ARC

(206-075-523-1 #1 FM Homing Antenna (LH)

AS-2487/ARC

(206-075-551-1) UHF Comm Antenna

AS-2670/ARC

(206-075-523-2) 01 FM Homing Antenna (RH)

AS-3188/ARN

(214-077-092-1) GS Antenna



BB-676/A Battery



ID-1351/A HRB Indicator

ID-1351C/A HRB Indicator

KIT-1A/TSEC IFF Computer CPO CPO

2-21

\

FM 101-20


TYPE NUMBER

OH-58

FUNCTION/NOUN

< oo in

K O

o oo o X O

9; ff-

;jp

AC

IC






RT-1285/APX-100 IFF Transponder


TSEC/KY-28 Comm Security Set CPO CPO

206-032-310-55 ADF Sense Antenna

206-075-518 VHF-AM & #1 VHF-FM Comm Ant

206-075-597-1 Audio Threshold System

206-075-716 Course Indicator

YG-1054D1 Proximity Warning System

2-22

FM 101-20


NOTEST

1. The AN/ARC-51 was installed in lieu of the AN/ARC-116 in some aircraft. 2. Equipment to be 100% installed in Europe. 3. The upper IFF antenna configuration was not firm at the time of this printing. It may be a AT-741 or a

contractor selected antenna in lieu of the AT-884. The lower IFF antenna will remain the AT-884.. 4. BB-649/A installed as part of winterization kit. 5. Equipment installed only in aircraft located at Ft. Bragg, Ft. Campbell, Ft. Hood and Ft. Rucker.

APPLICABLE AIRCRAFT AVIONICS MANUALS: TM 11-1520-228 Series

i

» »

2*23

FM 101-20


The following configuration depicts a typically configured TH-55A. The actual configuration may vary depending on peculiar geographic requirements or changes incorporated through MWO action and special purpose alterations.

;IV

TH-55A

>1 r "V

TYPE NUMBER FUNCTION/NOUN X H

MX-1646/AIC Headset Adapter

A-25A VHF Comm Antenna

12-GCAB-9E Battery

524A VHF-AM Radio Set

APPLICABLE PUBLICATIONS: DA Publications are not available.

2-24

FM 101-20


The following configuration depicts a typically configured UH-1 ( ) /EH-1 ( ). The actual configuration may vary depending on peculiar geographic requirements or changes incorporated through MWO action and special purpose alterations. !

UH-1


\y

<0

D at E

£ ö n x x

n x CO dS

£ ö m

PC X

to CO

X a; X

X à

É P3

>- b. X X X E- t- o CO CO

PC Q

PC X

Cc

>-

s Q

X P3

z >

É D

X X

X M



AN/APX-72 IFF Transponder ✓


AN/ARC-54/131 VHF-FM Radio Set #1 y AN/ARC-73 VHF-AM Radio Set CPO CPO

AN/ARC-102 HF-AM Radio Set CPO CPO CPO CPO CPO

AN/ARC-114 VHF-FM Radio Set #2 CPO CPO CPO CPO CPO CPO



AN/ARN-30 VOR Set

AN/ARN-59 ADF Set

2-23

FM 101-20


TYPE NUMBER

UH-1

FUNCTION/NOUN

to to D ai X

S ö m rH

S o

m D CO =8 O

s Q S X D

o o CO CO

cc a ü s S pH

K P

>- b D a X

>«

b X S l-H

as p

o 2

X D

X X

X w ■VI11 A .'J

AN/ARN-82 VOR Set

AN/ARN-83 ADF Set

AN/ARN-124 DME Set A:

AN/ARQ-33 Countermeasures Set





AS-3188/ARN

AT-640/ARN

GS Antenna

MB Antenna


AT-U08/ARC VHF-AM/UHF Antenna

BB-433A/A Battery


C-6533/ARC

C-8157/ARC

CU-942/ARC

CU-991/AR

Intercomm Set

Control-Indicator

FM Antenna Coupler

HF Antenna Coupler CPO CPO CPO 'CPO

2-26

FM 101-20


TYPE NUMBER

UH-1

FUNCTION/NOUN

<o p Pi X b s Ö CQ

ac 3

CQ 3 CZ3 «0

s Ö m

X 3

o CO CO

3 Oi X H X S

sc 3

>< OH 3 « 3 E-i r- o CO CO

X s

X 3

>-

fa X S

sc 3

o 2

X 3

X S

S fa

CU-1658/A HF Antenna Coupler 3CP0 CPO

CV-1275/ARN Converter

ID-250/ARN RM I

ID-998/ASN RM I

J-2 Gyro Compass Set

KIT-1A/TSEC IFF Computer CPO CPO CPO CPO CPO CPO

MC-1 Rate Gyro 11, 11, 11, 11, 11, 11,

MD-1 Displacement Gyro

MD-736/AR Signal Discriminator

MT-1719/AR Mount (CU-991) CPO CPO CPO 'CPO


MT-3772/A Mount (CU-1658) CPO CPO



PU-543/A Inverter

R-1041/ARN MB Set CPO CPO CPO CPO CPO CPO

R-1963/ARN MB/GS Receiver CPO CPO CPO


2-27

FM 101-20


TYPE NUMBER

UH-1

FUNCTION/NOUN

D at E H

U m

X D

n E <n 4

£ ö CO

É D

ee co E (H X

X p

X E

b. E « X H

X s

X B

>- ÖH

>-

X Q rH

X E

S o X

X B

X X

X w

■ye ;

T-366/ARC VHF-AM Radio Set


TSEC/KY-28 Comm Security Set CPO CPO CPO CPO CPO CPO

TSEC/KY-58 Comm Security Set CPO 3CPO ’CPO CPO CPO nCPO

205-075-325 ADF Sense Antenna

205-075-399 Audio Threshold System

205-706-027-1 HF Antenna CPO CPO CPO CPO CPO

206-075-543-3 FM Comm Antenna

YG1054D1 Proximity Warning System

FM 101-20


NOTES: 1. Proposed retrofit installation. 2. Provisions for the AN/ARC-102 system are not installed in FY 62 aircraft. 3. Proposed retrofit replacement for AN/ARC-73 and T-366. 4. AN/ARN-30, CV-1275 and AN/ARN-59 installed in UH-1B/C/M through 66-601 and UH-1D/H through

FY 65. AN/ARN-82 and AN/ARN-83 installed in subsequent aircraft. ;5. jj-2 installed in UH-1B/C/M through 66-15147 and in UH-lD/H through 66-16448. AN/ASN-43 installed ! in subsequent aircraft. '6. Provisions for the CU-1658 and MT-3772 installed in FY 68 and subsequent aircraft. 7. Proposed retrofit replacement for AN/ARC-51. 8. Proposed retrofit replacement for KY-28. 9. Equipment installed only in aircraft located at Ft. Bragg, Ft. Campbell, Ft. Hood and Ft. Rucker.

10. Only UH-1V peculiar avionics are listed. Other installed/CPO items will depend on the TMS of the aircraft selected for UH-1V designation which was not available at the time of this printing.

11. AU UH-1 ( ) aircraft were originally delivered with the MC-1 installed. However, it is presently being ■ removed (with no replacement) during depot overhaul.

i ' . " APPLICABLE AIRCRAFT AVIONICS MANUALS:

TM 11-1520-210 Series (Pertains to UH-lD/H) TM 11-1520-211 Series (Pertains to UH-1B/C/M)

i.

# 2-29

FM 101-20


The following configuration depicts a typically configured UH-60A. The actual configuration may vary depending on peculiar geographic requirements or changes incorporated through MWO action and special purpose alterations.

UH-60A


Xi'I.


AN/APN-209 (V) 2 Radar Altimeter

AN/APR-39(V)1 Radar Warning Set CPO


AN/ARC-114 VHF-FM Radio Set #2 CPO


AN/ARN-89 ADF Set

AN/ARN-123(V)1 VOR/MB/GS Set


AN/ASN-128 Doppler Nav Set



2-30

FM 101-20


TYPE NUMBER

UH-60A

FUNCTION/NOUN

< o <D

SC S3

CN-1314/A Gyro

C-1404/ARN-89 Compensator

KIT-1A/TSEC IFF Computer CPO

MT-3949/A

RT-1296/APX-100

RT-1167/ARC-164

Mount (KIT-1A)

IFF Transponder

UHF-AM Radio Set

TRU-2N/A Turn Rate Gyro


NOTES: 1. Complete provisions installed for 3 each KY-28 sets.

2. The AN/ARC-115 “Plain” version is not operationally compatible when used with communication security equipment. The AN/ARC-115A (V) 1 must be used.

GENERAL NOTE: The battery and most of the antennas and indicators installed in the UH-60A were furnished by the contractor. Applicable part numbers were not available at the time of this printing.

2-31

FM 101-20


The following configuration depicts a typically configured YAH-64. The actual configuration may vary depending on peculiar geographic requirements or changes incorporated through MWO action arid special purpose alterations.

YAH-64A



AN/APR-39(V)1 Radar Warning Set



AN/ARN-89B ADF Set

AN/ASN-128 Doppler Nav Set



KIT-1A/TSEC IFF Computer CPO

2-32

FM 101-20


TYPE NUMBER

YAH-64A

FUNCTION/NOUN

X < >>



RT-1156/APX-100 IFF Transponder



GENERAL NOTE: The YAH-64 was still in development at the time of this printing. Therefore, the configuration shown above is proposed only, not firm.

2-33

FM 101-20


The following configuration depicts a typically configured C-12A. The actual configuration may vary depending on peculiar geographic requirements or changes incorporated through MWO action and special purpose alterations.

C-12A


VHF-20B (Collins) VHF-AM Radio Set

G 4583 (Gables) VHF-AM Control

■G 4584 (Gables) VHF-AM Control

37R-2U (Collins) VHF-AM Antenna

35-5003 (Beech) VHF-AM Antenna

VIR-30AGM (Collins) VOR;MB/GS Set

VIR-30AG (Collins) VOR/GS Set

35-5017 (Beech) VOR Antenna

35-5016 (Beech) MB Antenna

37 P-5 (Collins) GS Antenna

331A-8G (CoUins) Course Indicator

331A-6P (Collins) Course Indicator

2-34

FM 101-20


C-12A


< e<

Ó D at

356F-3 (Collins) Audio Amplifier

356C-4 (Collins) Isolation Amplifier

DF-203 (Collins) ADF System c/o:

51Y-4A (Collins) Receiver

137 A-4 (Collins) Loop Antenna

614L-8 (Collins) ADF Control

97-340017-25 (Beech) ADF Sense Antenna

101-440019-15 (Beech) ADF Sense Antenna

DME-40 (Collins) Distance Measuring Equip

339F-12 (Collins) DME Indicator

237Z-1 (CoUins) DME Antenna

RT-1168/ARC-164 UHF-AM Radio Set CPO CPO

RDR-1200 (Bendix) Weather Radar c/o:

RT-1201A (Bendix) Rcvr-Transmitter and Mount

IN-1202A (Bendix) Indicator

AT-1203A (Bendix) Antenna

C-14-43 (Sperry) Compass System do:

656520 (Sperry) Flux Valve

2-35

FM 101-20


TYPE NUMBER

C-12A

FUNCTION/NOUN O

2587193-43 (Sperry) Gyro and Synchronizer

341C-1 (Collins) Servo Amplifier



AT-884 Antenna

718U-5 (Collins) HF-SSB Set c/o: .

671U-4A (Collins) Rcvr-Exciter and Mount

548S-3 (Collins) Power Amplifier and Mount

514A-4 (Collins) Control

AP-106 (CoUins) Integrated Flight System c/o:

344C-9A (Collins) Aileron Servo and Mount

344C-9A (Collins) Elevator Servo and Mount

344C-9A (Collins) Rudder. Servo and Mount

344D-6 (Collins) Elevator Tab Servo and Mount

332D-11A (Collins) Vertical Gyro

562C-13 (Collins) Computer and Mount

329T-1 (Collins) Turn and Slip Indicator

329B-9A (Collins) Flight Director Indicator

2-36

FM 101-20


C-12A


< a

Ó

-3

N

D

332C-10 (CoUins) RMI

356C-4 (Collins) Interphone Amplifier

356F-3 (Collins) Paging Amplifier

Emerg Locator Transmitter

NOTES: 1. Equipment installed in overseas areas. 2. The AN/APX-101 is installed in FY 73 aircraft and the AN/APX-100 is installed in all subsequent

aircraft.

GENERAL NOTE: The C-12A avionics configuration contains all commercial equipment. As such, data sheets for these items will not appear in this publication. Support of these items is the responsibility of the contractor.

APPLICABLE AIRCRAFT AVIONICS MANUALS: DA Publications are not available. Refer to applicable commercial literature.

2-37

FM 101-20


The following configuration depicts a typically configured OV-1 ( ) /RV-1D. The actual configuration may vary depending on peculiar geographic requirements or changes incorporated through MWO action and special purpose alterations.

OV-1


m > o

> o > «

AN/AAS-14 IR Detecting Set

AN/AAS-24 IR Detecting Set 4,14 CPO

AN/ADR-6 Radiac Set CPO

AN/AJA-5 Synchrophaser

AN/AKT-18 Data Transmitting Set

AN/AKT-18A Data Transmitting Set


AN/ALQ-136 Countermeasures Set CPO CPO

AN/ALQ-147(V)1 Countermeasures Set CPO

AN/ALQ-147(V)2 Countermeasures Set CPO



Sli‘

2-38

FM 101-20


{

\

OV-1


CQ

> O

> o > o > oi

AN/ALR-46 Radar Warning System CPO CPU

AN/APN-22 Radar Altimeter

AN/APN-171A(V)1 Radar Altimeter

AN/APR-44(V)3 Radar Warning System CPO CPO

AN/APS-94C Radar Surveillance Set

AN/APS-94D Radar Surveillance Set 4,14 CPO




AN/ARC-102 HF-AM Radio Set CPO CPO CPO CPO


AN/ARC-114 VHF-FM Radio Set #2 14 CPO



AN/ARN-30E VOR Set

AN/ARN-59 ADF Set

AN/ARN-82 VOR Set

AN/ARN-83 ADF Set

2-39

F&ä 101-20


TYPE NUMBER

OV-1

FUNCTION/NOUN

n > o

> at

AN/ARN-89 ADF Set

AN/ARN-103 TACAN Set

AN/ART-41A Data Transmitter

AN/ASN-33 Nav Computer Set

AN/ASN-Ü4 Doppler Nav Set

AN/ASN-76 Attitude Ref Set

AN/ASN-86 Inertial Nav Set

AN/ASW-12 Autopilot Set

AN/AYA-10 Data Annotation System 14 COP

AN/USQ-6I Digital Data System CPO



AT-134A/ARN MB Antenna

AT-326/ARN GS Antenna

AT-450/A Data Link Antenna

AT-74I/A IFF/TACAN Antenna

AT-I108/ARC VHF-AM/UHF Antenna

BB-433AyA Battery

2-40

FM 101-20


TYPE NUMBER

OV-1

FUNCTION/NOUN > O

u > o > o >

at





CU-1658/A HF Antenna Coupler CPO

DT-173/AJN Magnetic Azimuth Detector

ID-250/ARN RMI

ID-663/U BDH Indicator

KA-60C Camera 11

CPO

10 CPO

KIT-l'A/TSEC IFF Computer CPO CPO CPO CPO

KS-61A Photo Surv System 13

CPO

12,13

CPO

KS-104A Photo Surv System 12,13

CPO

KS-104B Photo Surv System 12,13

CPO

KS-113A Photo Surv System 13

CPO

1 MD-736/A Signal Discriminator CPO CPO

2-41

FM 101-20


TYPE NUMBER

OV-1

FUNCTION/NÖUN


MT-377Í/A Mount (CU-1658) CPO



OK-279/A Voltage Controller Grp

PU-544/A Inverter

PU-545/A Inverter

PU-750/A Inverter

R-844/ARN-58 MB/GS Set

R-1963/ARN MB/GS Set 15, 15. 16, 16,

RT-1167/ARC-164 UHF-AM Radio Set 16. 16 16, 16,

SA-521/A Antenna Switch

T-992/A True Airspeed Xmtr


TSEC/KY-28 Comm Security Set CPO CPO CPO CPO

TSEC/KY-68 Comm Security Set 17 CPO

17 CPO

17 CPO

17 CPO

134AV25518-1 ADF Sense Antenna

134AV35003-1 GS Antenna

2-42

FM 101-20


TYPE NUMBER

OV-1

FUNCTION/NOUN

CQ

> O

> o > o >

ai

134AV45511-5 HF Antenna

134CS30103-1 VOR Antenna

134SCAV247-1 FM Comm Antenna

r

;2-43

FM 101-20


NOTES:

1. Proposed retrofit installation. 2. Installed in selected aircraft only. 3. AN/APN-22 installed thru FY 67 aircraft. AN/APN-171 installed in FY 68 aircraft. 4. Either the AN/AAS-24 or the AN/APS-94D can be installed but not both. Equipment to be installed

will be issued on a TOE basis only. 5. OV-1C aircraft prior to FY 66 and all OV-1B have the AN/ARN-30E andd AN/ARN-59 instaUed. FY 66

and subsequent OV-1C aircraft have the AN/ARN-82 and AN/ARN-83 installed. The retrofit replacement of the AN/ARN-30E by the AN/ARN-82 in all applicable aircraft is proposed.

6. The AT-134 is modified to become 134AV25508-1. 7. The AT-326 (Collins 37P4) or the 134AV35003-1 is installed on OV-lC aircraft. 8. Either the DT-309 or DT-376 may be installed as a part of the DT-173. 9. The ID-250 is installed in lieu of the ID-663 in some OV-1B and OV-lC aircraft.

10. Provisions installed for 2 each KA-60C in addition to KS-113A system. 11. Installed in FY 66, FY 67 and FY 68 aircraft in addition to KS-61 or KS-104 ( ) systems. 12. KS-61A installed thru FY 66 aircraft. KS-104A installed in FY 67 aircraft and KS-104B installed in

FY 68 aircraft. 13. Some components of these systems are installed. However, the cameras and other major components

are issued on a TOE basis only. 14. Equipment issued on a TOE basis. 15. Proposed retrofit replacement for R-844. 16. Proposed retrofit replacement for AN/ARC-51. 17. Proposed retrofit replacement for TSEC/KY-28.

APPLICABLE AIRCRAFT AVIONICS MANUALS: TM 11-1510-204 Series (Pertains to OV-1B, C, D) TM 11-1510-213 Series (Pertains to RV-1D)

2-44

FM 101-20

2-2. Avionics and Surveillance Equipment Configurations (Cont.)

The following configuration depicts a typically configured T-41B. The actual configuration may vary depending on peculiar geographic requirements or changes incorporated through MWO action and special purpose alterations.

T-41B


n Tj*

É-1

AN/ARC-54/131 VHF-FM Radio Set CPO

AN/ARN-83 ADFSet

AS-1703/AR FM Comm Antenna CPO

AS-1922/ARC FM Homing Antenna CPO


CU-942/ARC FM Antenna Coupler CPO

ID-718/ARN Azimuth Indicator

0570400-605 VOR Antenna

0570401-5 ADF Sense Antenna

08700-60-1 Battery

515R VHF Comm/Nav Radio Set

901C Emerg VHF Radio Set

25060 (A-25A) Antenna

31640 (1N514R) Indicator

2-45

FM 101-20



DA Publications are not available.

2-46

FM 101-20


The following configuration depicts a typically configured T-42A. The actual configuration may vary depending on peculiar geographic requirements or changes incorporated through MWO action and special purpose alterations.

T-42A


< «


AN/ARC-51BX UHF-AM Radio Set CPO


•AN/ARN-30 (15F) VOR Set

♦AN/ARN-59 (21A) ADF Set

•AT-640/ARN (37X-2) MB Antenna

♦AT-1108/ARC (37R-2U) VHF/UHF Antenna

*BB-432/A (MS24496) Battery


»CV-1275/ARN (B-18A) Converter

•ID-250/ARN (36104-IL) RMI

*ID-998/ASN (C-6-H) RMI

2-47

FM 101-20


TYPE NUMBER

T-42A

FUNCTION/NOUN

< -i*

E-*

*PU-542/A (MS16057) Inverter

R-844/ARN-58 MB/GS Set

T-366/ARC VHF-AM Transmitter

A-138 VOR Antenna

C-1’4 Compass System

Ll11 ADF Loop Antenna

NOTES:

^Commercial equivalent, shown in parentheses, may be installed.


DA Publications are not available.

2-48

FM 101-20


The following configuration depicts a typically configured U-8 ( ). The actual configuration may vary depending on peculiar geographic requirements or changes incorporated through MWO action and special purpose alterations.

U-8


a CD

D

■g g Q 00

D

Ct- ao

g s b °P P

O oo P


AN/APN-158 Weather Radar


AN/ARA-54 Glide Slope Receiver






AN/ARC-102 HF-AM Radio Set CPO CPO CPO CPO CPO


AN/ARN-12/32 MB Receiver

AN/ARN-30 VOR Set

2-49

FM 101-20


TYPE NUMBER

U-8

FUNCTION/NOUN

h ao

«5 •o o s

-fa 00

O 00

AN/ARN-103 TACAN Set CPO1 CPO1

AN/ARN-59 ADF Set



AT-454/ARC FM Comm Antenna

AT-884/APX IFF/TACAN Antenna


BB-432/A Battery


C-8157/ARC Control Indicator CPO CPO


CU-991/ARC HF Antenna Coupler CPO CPO CPO

CU-1658/A HF Antenna Coupler CPO CPO

CV-1275/ARN Converter

ID-250/ARN RMI

ID-387/ARN Course Indicator ’CPO ‘’CPO

ID-663/A

ID-998/A

BDH Indicator

RMI

’CPO ’CPO

2-50

FM 101-20


TYPE NUMBER

U-8

FUNCTION/NOUN

Q 00 ¿

'S

■g S Q 00

fa* 00

g s o 00

KIT-1A/TSEC IFF Computer CPO CPO CPO CPO CPO

MD-736/AR Signal Discriminator

MT-1719/AR Mount (CU-991) CPO CPO CPO


MT-3772/A Mount (CU-1658) CPO CPO

MT-3802/ARC Mount (KY-28) CPO CPO


MX-1646/AIC Headset Adapter

PU-543/A Inverter

PU-544/A Inverter

R-33 Battery

R-104I/ARN MB Receiver

SB-329 Signal Dist Panel

T-366/ARC VHF-AM Transmitter


TSEC/KY-28

1-100A

1-101A

Comm Security Set

Inverter

Inverter

CPO CPO

2-51

FM 101-20


NOTES: 1. Either 1 ea ADF, l ea VOR and 1 ea TACAN or 2 ea ADF and 1 ea VOR or 2 ea VOR and 1 ea ADF

may be installed. 2. Either 2 ea ADF and 1 ea VOR or 1 ea ADF and 2 ea VOR may be installed. 3. The ID-387 and ID-663 are installed in lieu of the ID-250 with the TACAN, VOR and ADF configuraton.

GENERAL NOTE: The modernized configuration pertains to those aircraft which have had Avionics Standardization MWOs (ZYR/ZYU) appfied.

APPLICABLE AIRCRAFT AVIONICS MANUALS: TM 11-1510-201 Series

i

2-52

FM 101-20


The following configuration depicts a typically configured U-10A. The actual configurátion may vary depending on peculiar geographic requirements or changes incorporated through MWO action and special purpose alterations.

U-10A


< o

AN/ARA-31 FM Homing Antenna CPO

AN/ARC-44 VHF-FM Radio Set CPO

AN/ARC-51BX UHF-AM Radio Set CPO

•AN/ARC-73 VHF-AM Radio Set

•AN/ARN-30D VOR Set 1

AN/ARN-32 MB Receiver

*AN/ARN-59 ADF Set


•AT-1108/ARC VHF-AM/UHF Antenna

»BB-432/A Battery

C-1611/AIC

♦PU-542/A

Intercomm Set

Inverter

CD-4 Course Director

2-53

FM 101-20


NOTES:

♦Commercial equivalent may be installed.

APPLICABLE AIRCRAFT AVIONICS MANUALS: DA Publications are not available.

FM 101-20


The following configuration depicts a typically configured U-21( ) /RU-21 ( ). The actual configuration may vary depending on peculiar geographic requirements or changes incorporated through MWO action and special purpose alterations.

These configurations do not include mission equipment installed in the RU-21 series aircraft.

U-21& RU-21


O 3

D BJ

a <N

P

o

p tí

p tí

p tí

Eb, eji


AN/ALR-46 Radar Warning System

AN/APN-158 Weather Radar

AN/APR-25/26 Radar Warning Receivers CPO


AN/ARA-50 UHF DF Set CPO CPO CPO



AN/ARC-102 HF-AM Radio Set XPO


AN/ARN-82 VOR Set

AN/ARN-83 ADF Set

2-55

FM 101-20


U-21 & RU-21


o M

D Ct!

CM

D pci at

Left blank intentionally

AN/ARN-103 TACAN Set


AN/ASN-86 Inertial Nav System

AS-580/ARN VOR/GS Antenna



AS-2285/ARC FM Comm Antenna


AT-884/APX IFF/TACAN Antenna


BB-433/A Battery



CN-405/ASN Flux Compensator


CU-1658/A HF Antenna Coupler CPO

ID-250/ARN RMI

2-56


U-21&RU-21


O 3

at D cc

S3 tí tí

X »-H CN rH cq

ID-351/387 Course Indicator

ID-998/ASN RM I

KIT-1A/TSEC IFF Computer CPO CPO CPO CPO CPO CPO

MC-1 Rate Switching Gyro

MD-1 Displacement Gyro



MT-3772/A Mount (CU-1658) CPO



PU-543/A Inverter

PU-544/A Inverter

R-844/ARN-58 MB/GS Receiver

R-1963/ARN MB/GS Receiver


T-611/ASN Compass Transmitter

T-992/A True Airspeed Transmitter


2-57

FM 101-20


TYPE NUMBER

U-21 & RU-21

FUNCTION/NOUN D Pi

CN

P Pi

TSEC/KY-28 Comm Security Set CPO CPO CPO CPO CPO CPO

TSEC/KY-58 Comm Security Set CPO CPO CPO ?CPO| CPO °CPO

071-1034-00 (King) ADF Loop Antenna

1014A (Wilcox) Transponder

35-5003 (CCC) VHF Antenna

35-5016 (CCC) MB.Antenna

35-5017 (CCC) VOR/GS Antenna

35-5018 (CCC) DME/Transponder Antennas

50-345611 (Beech) ADF Sense Antenna

50-345615 (Beech) HF Antenna CPO

50-345764-1 (Beech) Main Inverter 6, 7.

50-345764-2 (Beech) Standby Inverter 6,7

50-345764-5 (Beech) Main Inverter 7.8

50-345764-6 (Beech) Standby Inverter 7,8

50-345772 (Beech) Mount (RT-698/ARC-102) CPO

50-345812 (Beech) ADF Sense Antenna 1

50-345974 (Beech) RM I

50-346063-3 (Beech) HF Antenna

2-58

FM 101-20


TYPE NUMBER

U-21 & RU-21

FUNCTION/NOUN

O

Ô ai

a

p d

u rH C4

P Pi

P Ctí

p pi

ta 04

D

51RV-2B (Collins) VOR/GS Set

51Z-6 (Collins) MB Set

91-340045-1 (Beech) HF Antenna

331A-3G (Collins) Course Indicator

331A-6P (Collins) Course Indicator.

356C-4 (Collins Isolation Amplifier

356F-3 (Collins) Speaker Amplifier

618M-2B (Collins) VHF-AM Radio Set

AP-105 (Collins) Autopilot

AVQ-55 (RCA) Weather Radar

C-14-3 (Sperry) Compass System

CA-5H (Marathon) Battery

D11220-1 Battery

DME-40 (Collins) DME Set

E551-11220-6 Battery

FD-108N (Collins) Flight Director

H-14 (Honeywell) Autopilot

KDF-800 (King) ADFSet

2-59

FM 101-20


U-21&RU-21


ca Ó cn

CD cq D D

X •OH

CN

Ó

KF-580 (King) ADF Control

MGH-182-100 (Leland) Inverter

MGH-229-100 (Leland) Inverter

PN-101 (Collins) Compass System

VC-1 SOW (Gables) Transponder Control

VC-270D-PS (Gables) VHF Control

VC-270D-XX (Gables) VHF Control

VT-10-02 VOR/GS Antenna 2 . . 2

2-60

FM 101-20


UV-18


< 00

RCA C-6533/ARC.3 Position Audio

Collins 356F-3,6 Speaker Public Address

King KY-175B VHF-AM/VOR/LOC #1

King KY-175B VHF-AM/VOR/LOC #2

King KN-74 R-NAV Computer

EDC DF-88 VHF Homer

Sunair ASB-100A HF/SSB/AM

AN/ARC-114 VHF-FM Comm

King KR-85 ADF#1

King KR-85 ADF #2

King KR-21 Marker Beacon

King KN-73 Glide Slope #1

King KN-73 Glide Slope #2

AN/APX-72 XPNDR

King KN-65 DME

Collins ALT-50 Radar Alt

King KI-525A & KCS-55A-01 Compass Pic. Nav.

Garrett Rescu 99/DAL DAL

2-61

FM 101-20


NOTES:

1. Utilizes a 50-345772 mount which is made from a PP-3702. 2. AN/ARN-52 may be installed in some aircraft. 3. Proposed retrofit replacement for R-844. 4. Proposed retrofit replacement for AN/ARC-51. 5. Proposed retrofit replacement for KY-28. 6. Installed in U-21A only. 7. Made from PU-545/A. 8. Installed in U-21 G only. 9. Made from ID-998/ASN.

GENERAL NOTE: The U-21F avionics configuration contains all commercial equipment. As such, data sheets for these items will not appear in this publication. Information pertaining to the support of these items is contained in AVSCOM Pamphlet 700-1.


TM 11-1510-209 Series TM 11-5825-252 Series (RU-21D Mission Equipment) TM 11-5865-216 Series (RU-21H Mission Equipment) TM 11-5895-809 Series (RU-21D Mission Equipment)

2-62

FM 101-20

2-3. Aircraft Armament.

The following aircraft armament subsystems and related components are either in the Research and Development stage, or have been type classified for field usage.

2-4. Aircraft Armament Application.

ARMT SS AIRCRAFT APPLICATION

UH-1 B C M D H

M5

M18A1

M21

M23

M24

M27

M28A1

M28A2

M35

M41

M156

M28A3

XM97E1

M19

M59

M128

M56

XM139

M136

XXX

XXX

X X

XXX

XX XX

X X

X X

AH-1 G S* S# SM

X X X X

X X

X X

X X

OH-6A OH-58 A C

CH-47 A B C D

YAH-64 A

XXX

Source (DRSAR-MAG)

2-63

FM 101-20

Aircraft Armament Application (cont)

ARMT SS AIRCRAFT APPLICATION

UH-1 B C M D H

X

X X

X X

M65

M22 X

M158A1 X

M200A1 X

XM260

XM135

XM261

XM 227

HMMS

*AH-1S (MOD) from AH-1G. models

#AH-1S new production

M AH-IS modernized from AH-1S (MOD)

AH-1 G S* S# S/W

X

X

X

X

X X

X X

X X

X X

X X

YAH-64

Source: (DRSMI-D)

2-64

FM 101-20

___ L ■ .¿»i. JJíLSXJ*. "tr II.Ií

<r rZ2s**

%

# , ^

®s í

Ä

5* »

AV 012011 . ¿à- * * • >/

Figure 2-1. M18A1 Armament subsystem

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AV 000139

Figure 2-2. MISAI Armament subsystem

2-65

FM 101-20

2-5. M18A1 Armament Subsystem.

ARMAMENT SUBSYSTEM : M18A1 APPLICABLE AIRCRAFT TYPE MODEL AND SERIES: Attack helicopter AH-1 SERIES AVERAGE PROCUREMENT PRICE: $20,070 TYPE CLASSIFICATION: Standard LOGISTIC CONTROL CODE. A

NOMENCLATURE: Armament pod, helicopter, 7.62mm machine gun: high-rate

DESCRIPTION: The M18A1 armament pod consists of one 7.62mm automatic gun, M134, in a cylindrical pod mounted on the inboard wing stores of the aircraft. The pod stores 1500 rounds of ammunition in a linkless feed system. The gun is electrically driven at either low rate, 2000 shots per minute, or high rate, 4000 shots per minute. The pod is self-powered by a self contained battery with a power start feature using auxiliary aircraft power for more starting torque. The pod is rigidly mounted and aiming is accomplished by maneuvering the aircraft.

CHARACTERISTICS: MAXIMUM EFFECTIVE RANGE: ELEVATION: MUZZLE VELOCITY: RATE OF FIRE: TRAVERSE: EMPTY WT: 240 lbs AMMUNITION:

TYPE: CAPACITY: SIGHTING:

1500 meters Fixed 2750 FPS 2000 or 4000 SPM Fixed LOADED WT: 320 lbs

Linked 7.62mm 1500 rds M73 Reflex type

MAINTENANCE AND SUPPLY: Maintenance instruction: Repair parts: Special tools Shop sets: Not Applicable

AVUM TM 9-1005-257-12 TM 9-1005-257-20P TM 9-1005-257-20P

AVIM and Depot Support TM 9-1005-257-35 35P 35 and 35P

MODIFICATION DATA REQUIRED FOR INSTALLATION, FUNDING, CONTROLS, AND OPERATING INSTRUCTIONS:

KIT NSN PUBLICATION NICP 1005-00-832-7498 TM 9-1005-257-12 I B14

FUND REQUIREMENTS DA controlled

Operational instructions for subsystem can be found in TM 55-1520-221-10.

2-66

FM 101-20


ARMAMENT SUBSYSTEM: M28A2 APPLICABLE AIRCRAFT - TYPE, MODEL, SERIES: AH-1Q AVERAGE PROCUREMENT PRICE: $183,567 TYPE CLASSIFICATION: Standard

NOMENCLATURE: Armament subsystem, helicopter, 7.62mm machine gun, 40mm grenade launcher.

DESCRIPTION: The M28A2 armament subsystem is an electrically controlled, hydraulically operated, dual weapon that provides wide angle coverage and rapid fire for the AH-1Q TOW/Cobra. The M28A2 armament subsystem consists of a power operated chin turret, mounting the 7.62mm machine gun M134 and on the right and the 40mm grenade launcher Ml29 on the left. Ammunition is stored in the ammunition bay and moved to the turret through fixed and flexible chuting. The M28A2 is controlled in the flexible mode by either the gunner or pilot by use of the M128 helmet sight subsystem. The gunner can also direct fire by using the telescopic sight unit. The M-73 sight gives the pilot the ability to fire the turret weapons in the stowed position. The system provides the AH-1Q TOW/cobra with area and point fire for attack on personnel and lightly armored and unarmored materiel targets during escort and armed reconnaissance missions.

CHARACTERISTICS: MAXIMUM EFFECTIVE RANGE: 7.62rnn 1500 meters; 40rtm 1500 meters ELEVATION/DEPRESSION: +20° — 50° variable with traverse MUZZLE VELOCITY: Machine gun 2750 FPS 40mm Grenade launcher

RATE OF FIRE: TRAVERSE: EMPTY WT:

790 FPS 7.62mm - 2000 or 4000 SPM, 40mm - 420 SPM 110° left and right of longitudinal axis of AH-1G

7.62mm and 40mm 447 lbs LOADED WT: 897 lbs

AMMUNITION: CAPACITY:

TYPE: SIGHTING:

Maximum 4000 rds for each M 134, 300 rds for each M129. Linked 7.62mn and 40mm. Ml28 helmet sight subsystem M73 reflex sight M65TOW missile subsystem

2-67

FM 101-20

2-6. M28A2 - Armament Subsystem (Cent).

MAINTENANCE AND SUPPLY:

Maintenance Instruction: Repair parts: Special tools: Shop sets:

AVUM TM 9-1090-203-12-1 TM 9-1090-203-20P-1 TM 9-1090-203-12-1 and 20P-1 Not Applicable

AV1M and Depot -34-1AH-1Q Supplements -34-1 AH-IQ Supplements

Not Applicable


KIT NSN PUBLICATION NICP FUND REQUIREMENTS 1090-00-081-1046 TM 9-1090-203-12-1 B14 DA Controlled

Operation instructions are contained in TM 55-1520-221-10-1.

2-68

FM 101-20


ARMAMENT SUBSYSTEM: M28A1 APPLICABLE AIRCRAFT - TYPE, MODEL, SERIES: AH-1G AVERAGE PROCUREMENT PRICE: $95,067 TYPE CLASSIFICATION: Standard LOGISTIC CONTROL CODE: A

NOMENCLATURE: Armament subsystem, helicopter, 7.62mm machine gun, 40mm grenade launcher.

DESCRIPTION: The M28A1 armament subsystem is an electrically controlled, hydraulically operated, dual weapon that provides wide angle coverage and rapid fire for the AH-1G Hueycobra. The M28A1 armament subsystem consists of a power operated chin turret, mounting the 7.62 mm machine gun Ml34 on the right and the 40mm grenade launcher Ml29, on the left. Ammunition is stored in the ammunition bay and moved to the turret through fixed and flexible chuting. Fire control equipment is located at the gunner/co-pilot station and allows the gunner to train the weapons in azimuth and elevation. Provisions are made for the pilot to fire the weapons in the stow position. The system provides the AH-1G Hueycobra with area and point fire for attack on personnel and lightly armored and unarmored materiel targets during escort and armed reconnaissance missions.

CHARACTERISTICS: MAXIMUM EFFECTIVE RANGE:7.62mm 1500 meters;40mm 1500 meters ELEVATION/DEPRESSION: Variable elevator traverse, +12° to +17.5° and

depression —50°.

MUZZLE VELOCITY: Machine gun 2750 FPS 40mm Grenade launcher 790 FPS

RATE OF FIRE: 7.62mm - 2000 or 4000 SPM, 40mm - 420 SPM TRAVERSE: 114° left and right of longitudinal axis of AH-1G EMPTY WT: 7.62mm and 40mm 447 lbs LOADED WT: 897 lbs

AMMUNITION: CAPACITY:

TYPE:

SIGHTING:

Maximum 4000 rds for M134.300 rds for Ml 29. Linked 7.62mm and 40mm. Pilots reflex sight M73, lighted reticle and manual

range adjustment. Gunner sight is a flexible reflex

sight with automatic air speed compensation.

2-69

FM 101-20

2-7. M28A1 Armament Subsystem (Cent).



AVUM Avim and Depot TM 9-1090-203-12; -34 TM 9-1090-203-20P; -34P TM 9-1090-203-12 and 20P; -34 and -34P _ Not Applicable DMWR 9-1090-203


'■ KIT NSN PUBLICATION NICP FUND REQUIREMENTS

1090-00-134-3071 TM 9-1090-203-12 B14 DA Controlled ?" Operation instructions are contained in TM 55-1520-221-10.

AV 000149

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A k11

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J

M28A1

Figure 2-3. M28A1 Armament subsystem

2-70

FM 101-20

Á’/V

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n 1

Sí

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Figure 2-4. M35 Armament subsystem

2-71

FM 101-20

2-8. M35 Armament Subsystem.

ARMAMENT SUBSYSTEM: M35 APPLICABLE AIRCRAFT - TYPE, MODEL, SERIES: AH-1G AVERAGE PROCUREMENT PRICE: $44,865 TYPE CLASSIFICATION: Standard LOGISTIC CONTROL CODE: B

NOMENCLATURE: Armament subsystem helicopter, M35

DESCRIPTION: The M35 Subsystem has a 20mm Gatling type gun mounted on the inboard station of the left hand wing. The gun is basically a modified M61A1 gun with shorter barrels and a declutching feeder. It is designated the 20mm automatic gun, M195. It automatically clears itself of all live rounds at the end of each burst without dumping live rounds overboard. The gun is a fixed mount and is pilot controlled. Controls are provided for the co-pilot/gunner to fire the weaspon, if necessary. Two ammunition cans (one on either side) are faired into the fuselage at the base of the stub wings.

CHARACTERISTICS: EFFECTIVE RANGE: ELEVATION: MUZZLE VELOCITY. RATE OF FIRE: TRAVERSE:

3000 meters Attitude of aircraft 3380 FPS 650-850 SPM Attitude of aircraft

EMPTY WT: AMMUNITION: CAPACITY: TYPE: SIGHTING:

555 lbs (approx) LOADED WT: 1187 lbs (approx)

950 rds Linked 20mm — M56 HEI and XM220 TPT M73 reflex type



Organizational TM 9-1005-299-12 TM 9-1005-299-20P TM 9-1005-299-20P Not Applicable

Direct, General, and Depot Support TM 9-1005-299-34 -35P* -34 and -35P*


KIT NSN PUBLICATION NICP A 1560-00-246-4744 MWO 55-1520-22 MO/4 B17 C 1005-00-133-8193 TM 9-1005-299-12 B14

FUND REQUIREMENT COBRA Project Manager (DRCPM-CO)

Operational instructions are contained in TM 55-1520-221-10. • To be published as a -34P

FM 101-20

2-9. XM40 Remote Fuze Setter Subsystem, Helicopter, 2.75 Inch Rocket Launcher.

Not applicable.

j;

•d lUI

r..

2-73

FM 101-20

Deleted

Figure 2-5. XM40 Remote Fuze Setter Components

2-74

FM 101-20

fe

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M24

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M41

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Figure 2-6. M-24 and M-41 Armament subsystems installed on CH-47 (Chinook) helicopter

2-75

FM 101-20


ARMAMENT SUBSYSTEM: M24 APPLICABLE AIRCRAFT - TYPE, MODEL, SERIES: CH-47A AVERAGE PROCUREMENT PRICE: $3722 TYPE CLASSIFICATION: Standard ;

LOGISTIC CONTROL CODE: A “ ï

NOMENCLATURE: Armament subsystem, helicopter, door pintle mounted 7.62mm M60D machine gun

DESCRIPTION: The subsystem consists of two machine guns, M60D, and two mounts, one mount on each side of the aircraft. The subsystem mount assemblies are located iiT the cabin doorway and forward escape hatch of the CH-47 type helicopter. The subsystem contains mechanical safeties and stops to preclude accidental damage to the aircraft due to inadvertent firing of the guns into the airframe.. The mount assemblies are designed so that the left and right cams and stops cannot -be installed and used incorrectly on the opposite side of the aircraft. The machine gun with bipod has the capability of being quickly removed from the mount and used as a ground weapon. A link and brass ejection control bag is attached to the right side of each machine gun to prevent the cartridge cases and links from being ejected into the paths of the rotor blades or turbine engine intake.

CHARACTERISTICS: MAXIMUM EFFECTIVE RANGE: 1100 meters ELEVATION: Forward +3°, Aft +6.5°, Depression 78° right side,

67° left side MUZZLE VELOCITY: RATE OF FIRE: TRAVERSE:

2750 FPS 550 SPM Left gun 71° fwd, 59° aft; right gun 74° fwd, . 61° aft

EMPTY WT: 97 lbs AMMUNITION: CAPACITY: TYPE: SIGHTING:

LOADED WT: 123 lbs

200 rds per side Linked 7.62mm Ring and post type

MAINTENANCE AND SUPPLY: Maintenance Instructions Repair parts: Special tools: Shop sets:

AVUM AVIM and Depot TM 9-1005-262-14 TM 9-1005-262-24P TM 9-1005-262-24P Not Applicable


None required

KIT NSN PUBLICATION NICP FUND REQUIREMENTS 1005-00-763-1404 TM 9-1005-262-15 B14 DA ControUed


2-76

FM 101-20

2-11. M41. Armament Subsystem.

ARMAMENT SUBSYSTEM: M41 APPLICABLE AIRCRAFT - TYPE, MODEL, SERIES: CH-47A/B/C AVERAGE PROCUREMENT PRICE: $2,205 TYPE CLASSIFICATION: Standard

LOGISTICXONTROL CODE: A

NOMENCLATURE: Armament subsystem, helicopter, 7.62mm machine gun M60D, ramp mounted, light

s - weight. 4 .

— ~ i : •• '

DESCRIPTION: The M41 armament subsystem consists of a pintle mount, machine gun M60D, link and Jb-. < brass retainer, ammo box, and gunner’s safety harness. The machine gun M60D, is utilized

.3b with positive mechanical stops to limit weapon attitude.

CHARACTERISTICS: . . i

■

‘5/1

¿nifh

MAXIMUM EFFECTIVE RANGE: 1100 meters ELEVATION/DEPRESSION : MUZZLE VELOCITY: RATE OF FIRE: TRAVERSE: WEIGHT: AMMUNITION: CAPACITY:

+ 12.5°,-69°. 2750 FPS 550 SPM cyclic rate 52° right or left 41 lbs empty, 55 lbs loaded

200 rds TYPE: Linked 7.62mm SIGHTING: Aircraft ring and post type

MAINTENANCE AND SUPPLY: Maintenance Instruction: Repair parts: Special tools: Shop sets:

AVUM AVUM TM 9-1005-262-14 TM 9-1005-262-24P TM 9-1005-262-24P Not Applicable


KIT NSN PUBLICATION NICP FUND REQUIREMENT C 1005-00-087-2046 TM 9-1005-262-24P B14 DA Allocated

Operating instructions are contained in TM 9-1005-262-15.

2-77

FM 101-20

HELICOPTER REFLEX SIGHT M70

SEE DETAIL D

SEE DETAIL A

« A DETAIL

SEE DETAIL SEE DETAIL C

RAM AIR DUCT

DETAIL C

MOUNT ASSEMBLY

GUN ASSEMBLY

V D DETAI

m DETAIL B AV 012373

Figure 2-7. M27 Armament system components (OH-6A application)

2-78

FM 101-20 '

HELICOPTER REFLEX SIGHT M70

DETAIL D

SEE DETAIL D

y SEE DETAIL A

U \ SEE DETAIL C

SEE DETAIL B

GUN ASSEMBLY

MOUNT ASSEMBLY RAM AIR DUCT

DETAIL DETAIL C

DETAIL A

Figure 2-8. M27 (OH-58A application)

2-79

FM 101-20


ARMAMENT SUBSYSTEM: M27 APPLICABLE AIRCRAFT - TYPE, MODEL, SERIES: OH-6A, OH-58A AVERAGE PROCUREMENT PRICE: $25,439 TYPE CLASSIFICATION: Standard LOGISTIC CONTROL CODE: B

NOMENCLATURE: Armament subsystem, helicopter, 7.62mm machine gun; high rate M27

DESCRIPTION: The M27 armament subsystem mounts the high rate of fire 7.62mm machine gun M134. The subsystem consists of a single, remote controlled, semi-flexible mount which supports the machine gun, Ml34, on the left (port) side of the OH-6 and OH-58 helicopters. Linked 7.62mm ammunition is stored inboard and transported to the gun through fixed chuting. A flexible, mechanically linked sighting system enables the pilot to remotely aim and fire the machine gun. The weapon subsystem is flexible in elevation and depression only, being fixed in azimuth. The aircraft must be aimed by the pilot for target engagement. The armament subsystem is adaptable to the helicopter by means of quick release attachments. Complete internal provisions are incorporated in the production aircraft to accept the armament subsystem without modifications. The weapons subsystem complements weapon systems currently employed in the field.

CHARACTERISTICS: MAXIMUM EFFECTIVE RANGE: ELEVATION/DEPRESSION:

MUZZLE VELOCITY: RATE OF FIRE: TRAVERSE: EMPTY WT: 100 lbs AMMUNITION: CAPACITY: TYPE: SIGHTING:

1500 meters OH-6A +10°, to -24° OH-58 A +5 1/2° to-20° 2750 FPS 2000 or 4000 SPM None LOADED WT: 234 lbs

2000 rds. Linked 7.62mm Pilot M70 reflex type


AVUM TM 9-1005-298-12 TM 9-1005-298-20P TM 9-1005-298-20P Not Applicable

AVIM and Depot -34 -35P -35P DM WR 9-1005-298


KLF NSN C 1005-00-933-6242

PUBLICATION TM 9-1005-298-12

NICP B14

FUND REQUIREMENT DA Allocated

2-80

FM 101-20

2-13. UH-1B, C, and M Armament Configurations.

M-5 M-21 XM-156

Figure 2-9. UH-1B, C, and M Armament configurations

2-81

FM 101-20

AMMUNITION TRANSITION CHUTE

AMMUNITION CHUTE COVER

REAR AMMUNITION CHUTE ASSEMBLY

AMMUNITION BOOSTER ASSEMBLY

FRONT AMMUNITION CHUTE ASSEMBLY

ROTARY AMMUNITION

CAN

SIGHT MOUNT BRACKET ASSEMBLY

HAND CONTROL SIGHT ASSEMBLY

AMMUNITION CHUTE RETAINER

SERVO-AMPLIFIER JUNCTION BOX

ASSEMBLY AMMUNITION

CHUTE BRACKET s'

AMMUNITION CHUTE BRACKET

ASSEMBLY ^

AMMUNITION FEED CHUTE ASSEMBLY cn

E5ï$y y

AIR SPEED TRANSDUCER

I TURRET

ASSEMBLY

027

\

40 MILLIMETER GRENADE LAUNCHER

M75

TURRET CONTROL PANEL ASSEMBLY

Figure 2-10. M5 Armament subsystem components on UH-1B/C/M (Iroquois) helicopter.

2-82

FM 101-20

2-14. M5 Armament Subsystem, Grenade Launcher.

ARMAMENT SUBSYSTEM: M5 APPLICABLE AIRCRAFT - TYPE, MODEL, SERIES: UtUity UH-1 B/C/M AVERAGE PROCUREMENT PRICE: $41,607 TYPE CLASSIFICATION: Standard LOGISTIC CONTROL CODE. A

NOMENCLATURE: Armament subsystem, helicopter, 40 millimeter grenade launcher. Nose mounted turret (1 launcher). M75 Grenade Launcher, air cooled, electric motor driven.

DESCRIPTION: The MS is used on the UH-1 B/C/M helicopters, and consists of a flexible remote controlled, servo-power driven gun turret mounted in the nose of the UH-1B/C/M helicopters. The turret incorporates one M75 grenade launcher. Linked ammunition is stored in a rotary ammo drum in the cargo hook hole, pulled through a flexible chute by an ammo booster, and fed to the grenade launcher. The system also has a box feed system in addition to the rotary AMMO drum. A master armament control panel is located in the instrument console and is accessible to both the pilot and copilot gunner. A flexible hand control sight assembly mounts above the co-pilot’s seat from which the co-pilot can sight and fire the system. The subsystem can also be fired in the stow position by either the pilot or co-pilot by means of a trigger switch on both cyclic stick

. grips. In this mode, the turret is flexible in elevation. An MWO has been applied to the 1 r subsystem to give the sight lead angle compensation. A dual range reticle has been applied

for more accuracy at long range.

CHARACTERISTICS: \ EFFECTIVE RANGE:

ELEVATION/DEPRESSION : MUZZLE VELOCITY: RATE OF FIRE: TRAVERSE: EMPTY WT: Box Fed: 233 lbs

Rotary Drum Fed: 223 lbs

AMMUNITION: TYPE: CAPACITY: SIGHTING:

1500 meters +15°, -35° 790 FPS 230 SPM 60° right and left LOADED WT: 335 lbs (*150 rds)

459 lbs (**300 rds)

Linked 40mm ammunition. *150 rds **300 rds respectively Reflex type: gunner/co-pilot operated in elevation and deflection.

MAINTENANCE AND SUPPLY: a. Maintenance

Instruction: b. Repair parts: c. Special tools: d. Shop sets: Not Applicable

AVUM AVIM and Depot TM 9-1010-207-12 Support TM 9-1010-207-35 TM 9-1010-207-12,20P 34P TM 9-1010-207-12,20P 34P

2-83

FM 101-20

2-14. M5 Armament Subsystem, Grenade Launcher (CONT).


KIT NSN A 1560-00-753-7294 C 1010-00-738-5811 •RAC 1560-00-936-4334

PUBLICATION NICP MWO 55-1520-211-34/33 B17 TM 9-1010-207-12 B14 MWO 55-1520-211-30/32 B17

FUND REQUIREMENTS DA Allocated DA Allocated DA Controlled-

Initial issue of kits is DA Controlled and Procurement Appropriation Army (PAA) funded. Repair parts other than initial MWO procurement items are stock funded.

•RAC — Rotary Ammo Can — Required to upgun the M5 subsystem.

Operational instructions for subsystem can be found in TM 66-1520-220 series manual.

2-84

FM 101-20

r V

Figure 2-11. M19 Dispenser

2-85

J

FM 101-20

2-15. M19 Dispensing Subsystem.

Dispenser: Aircraft:

M19 UH-l/B/C/D/H

Average procurement price: $1,500 Application: Flares per dispenser: Weight:

One in troop cargo compartment 24 Flares, MK45 w/adapter 150 lbs empty 822 lbs with flares 118 inches w/snout extended 81.0 inches w/snout collapsed 16.0 inches 46.0 inches Manually controlled

Overall Length:

Width: Height: Rate of Ejection:

Elevation: Transverse:

Attitude of aircraft Attitude of aircraft Visual assessment Sighting:

Status: DOD1C:

LP L106

DESCRIPTION: MK45 Flares are loaded into the dispenser with pull cable assembly disk inserted in the overhead track. Immediately prior to launch, the flare safety pin is pulled. The flare to be launched is positioned so that its base is stopped by the foot on the base tray. The operator then pushes the upper portion of the flare outward. The base of the flare then swings outward, providing sufficient force on the pull cable assembly to shear a pin, permitting the flare to fall free. A pull pin is provided for manual jettisoning of the load and flare rack.

the safety pin removed. When launched, the weight of the falling flare against the pull cable exerts sufficient force to break a shear pin to initiate the delay and subsequently ignite the fuze. At the desired time, the parachute/candle assembly is ejected from the outer container, and activated. Near the end of burning, the parachute is collapsed and the spent flare falls rapidly to the ground.

MK45 Flare, Aircraft, Parachute.

Weight: Overall Length: Diameter: Adjustable Time:

Illumination: Burn time:

2,000,000 candlepower 210 seconds 28 lbs 36 inches 4.87 inches Mechanical/pyrotechnic fuze

Status: Logistic

Std

Control Code: DODIC:

B 1370-L424

DESCRIPTION: Prior to launch, the fuze is set for the desired drop delay (in feet below the aircraft), and

2-86

Figure 2-12. M21 Armament subsystem installed on UH-1B/C/M (Iroqouis) helicopter

Miß

■il

2-87

FM 101-20


ARMAMENT SUBSYSTEM: M21 APPLICABLE AIRCRAFT - TYPE, MODEL, SERIES: Utility aircraft, UH-1B, C, M AVERAGE PROCUREMENT PRICE: $51,897 TYPE CLASSIFICATION: Standard LOGISTIC CONTROL CODE: A

NOMENCLATURE: Armament subsystem, helicopter, 7.62mm twin high rate machine gun with 2.75 inch rocket launchers.

DESCRIPTION: The M21 armament subsystem combines the 7.62 mm, high rate of fire machine gun M134 and the 2.75 inch Folding Fin Aerial Rocket (FFAR), M158A1 launchers. The subsystem consists of two remotely controlled, power operated, flexible pylons, each mounting one 7.62mm machine gun Ml34 and provisions for a non-flexible rocket pod containing seven 2.75 inch FFAR. The rocket launcher installation on each pylon contains associated hardware to fire the rockets and to jettison the launcher. Linked 7.62mm ammunition is stowed inboard and transported to the guns through flexible chuting. A flexible sighting system enables the copilot to remotely aim and fire the machine guns. The pilot may fire either the rockets or the machine guns when in stow position using a fixed sight. The subsystem utilizes all standard 7.62mm NATO ammunition and 2.75 inch rockets applicable to the M158A1 launcher.

CHARACTERISTICS: MAXIMUM EFFECTIVE RANGE: Machine Gun: 1500 meters Rocket: 3000 meters RATE OF FIRE: MUZZLE VELOCITY: TRAVERSE:

SIGHTING:

EMPTY WEIGHT: 804 lbs AMMUNITION: TYPE: CAPACITY: ROCKETS: TYPE: CAPACITY:

ELEVATION DEPRESSION: Machine Gun: +10° to -85° Rocket Launcher: Boresight only 2000 or 4000 SPM 2750 FPS Machine guns, inboard 12°, outboard 70° in à azimuth from longitudinal axis Pilot-manual reflex type for machine gun and rocket. Copilot/gunner flexible reflex type sight for machine gun only LOADED WEIGHT: 1179.2 lbs

Linked 7.62MM 6000 rds

2.75 inch FFAR 14 RDS

2-88 L<~

FM 101-20

2-16. M21 Armament Subsystem (CONT).

MAINTENANCE AND SUPPLY: Maintenance Instruction: Repair Parts:

- • Special Tools: To be published

AVUM TM 9-1090-202-12 TM 9-1090-202-20P TM 9-1090-202-20P

AVIM and Depot Support TM 9-1090-202-35 -34P* -34P*

II


KIT NSN A 1560-00-915-8931 B .1560-00-915-8933 C ... : 1090-00-923-5971

-• *1560-00-923-3182

PUBLICATION NICP MWO 55-1520-211-30/8 B17 TM 55-1520-211-20/5 B17- TM 9-1090-202-12 B14 MWO 55-1520-211-30/12 B17

FUND REQUIREMENT DA Allocated DA Allocated DA Allocated Free Issue

Initial issue of kits is DA Allocated, DA Controlled, and Procurement Appropriation Army (PAA) funded. Repair parts other than initial MWO procurement items are stock funded.

Operational instructions for subsystem can be found in TM 55-1520-220 series manual.

*Sight Stow Bracket required if not previously installed.

In addition to the above, these modifications can be installed only in aircraft which have the following provisions:

M3/M6 “A” Kit, FSN 1560-9604043, publication MWO 55-1520-22140/4, NICP B17, DA Allocated Ml6 “A” Kit, FSN 1560-918-7007, publication MWO 55-1520-211-30/4, NICP B17.

Initial issué bf rocket launchers, M158A1, FSN 1055-805-0689, is provided with subsystem.

2-89

FM 101*20

MC

Figure 2-13. M22 Armament system installed on UH-1B/C (Iroquois) helicopter

■- .t ■■

2-90

FM 101-20

2-17. M22 Armament Subsystem, Guided Missile Launcher.

ARMAMENT SUBSYSTEM: M22 APPLICABLE AIRCRAFT - TYPE, MODEL, SERIES: UH-1B/C AVERAGE PROCUREMENT PRICE: $34,000 (estimate) TYPE CLASSIFICATION: Standard LOGISTIC CONTROL CODE: A

NOMENCLATURE: Armament subsystem, helicopter, guided missile launcher.

DESCRIPTION: The M22 system includes a guidance control box, missile selector box, control stick, and six launchers. Items required to complete the airborne subsystem are an MK-8 pilots sight,

■ a stabilized optical 6X sight for the gunner, two booms for mounting launchers (three per side), and jettisoning equipment. An adaption kit is required for attachment of system components to the helicopter. Operation of the subsystem requires close coordination between pilot and co-pilot/gunner.

CHARACTERISTICS: EFFECTIVE RANGE: ELEVATION: MISSILE VELOCITY: RATE OF FIRE: TRAVERSE: EMPTY WT: 272 lbs MISSILE CAPACITY: AMMO TYPE: SIGHTING:

DATA:

3000 meters Missile directed in flight by wire command link. 180 meters/second cruise As selected by pilot/gunner. Missile directed in flight by wire command link. LOADED WT: 650 lbs 6 missiles (3 each side) AGM-22B Missile, 63 lbs each Pilot MK8 lighted roof mounted. Co-pilot/gunner 6x42 power anti-collision binocular (M-55) or monocular (M-58.) Complete outboard stores are jettisonable, or each missile.

MAINTENANCE AND SUPPLY: Maintenance instruction:

Repair parts: Special tools: Shop sets:

AVUM A VIM support TM 9-1400-461-20 and -35 TM 9-1400-461-12P and -35P TM 9-1400-461-12P and -35P TM 9-1400-461-12P and -35P

MODIFICATION DATA REQUIRED FOR INSTALLATION, FUNDING, CONTROLS, AND OPERATING

INSTRUCTIONS: Operational Instructions contained in TM 55-1520-219-10 and TM 55-1520-220-10 manuals.

i

2-91

FM 101-20

f/

Figure 2-14. M156 Armament subsystem (Shown with M200A1 rocket launcher)

2-92

FM 101-20

HELICOPTER CABIN ROOF (REFERENCE)

INFINITY REFLEX SIGHT ROOF

SIGHT (STOWED) MOUNT (STOWED)

<7

PNO7

V <7

0

9 I e*»

0 &

ARM PANEL INTERVALOMETER CONTROL PANEL

LEFT-HAND RACK AND SUPPORT ASSEMBLY

Figure 2-15. M156 Armament subsystem components

#

2-93

FM 101-20


ARMAMENT SUBSYSTEM: M156 APPLICABLE AIRCRAFT: UH-1B/C/M AVERAGE PROCUREMENT PRICE: $10,595 TYPE CLASSIFICATION: Limited Procurement LOGISTIC CONTROL CODE: U

NOMENCLATURE: Mount, multiarmament, helicopter

DESCRIPTION: This item consists of two separate mounts, one mount instalied on each side of the UH-1 helicopter. It is capable of carrying and firing the M158A1 and M200A1 2.75 inch rocket launchers or carrying external stores suspended from 14 inch bomb racks, MA-4A. The external stores cannot exceed 540 lbs per mount. A product improvement proposal which will enable the Ml56 to carry a fully loaded 19 tube rocket launcher using the new heavy warhead rocket has been evaluated for incorporation into the subsystem.

CHARACTERISTICS: EFFECTIVE RANGE: ELEVATION: TRAVERSE: EMPTY WEIGHT: LOADED WEIGHT: SIGHTING:



MODIFICATION DATA:

ORGANIZATIONAL INSTRUCTIONS:

Not applicable Fixed Fixed 82 lbs without launcher 540# per mount, maximum XM60 Reflex

AVUM TM 9-1090-204-12 TM 9-1090-204-20P TM 9-1090-204-20P Not applicable

AVIM and Depot -34 -35P -35P

TM 55-1520-219-10. TM 55-1520-220-10.

REMARKS: For Rocket Loading information, see figure 2-32, 2.75 inch Rockets and Rocket Launchers.

#

2-94

FM 101-20

2-19. M158A1, 2.75 Inch Rocket Launcher (7-Tube).

Rocket Launcher: M1S8A1 Aircraft Series: UH1B/C/M Average Procurement Price: $382.

Type Classification: STD A Logistic Control Code: A

AH-1

Nomenclature: Launcher, Rocket Aircraft, 2.75 Inch — M158A1 (7-Tube).

Description: Thé M158A1 is a reparable 7-tube 2.75 inch rocket launcher used on the UH1/B/C/M and AH1 Aircrafts. It is 58 inches long and weighs 48 lbs.

Remarks: TOE Authorization - not available this printing.

Basis of Issue: Approved BOI not available. For planning purposes: 2 each per UH-IB/C/M armed with M21 Subsystem. 1 each per AH-1 aircraft (all).

Figure 2-16. Launcher, rocket aircraft, 2.75 inch-M158Al (7-tube)

2-95

FM 101-20

2-20. M200A1 2.75" Rockat Launcher (19-Tube).

Rocket Launcher: Aircraft Series: Reprocurement Price:

Type Classification: Logistic Control Code:

M200A1 UH1B/C/M AH-1 $1,683, subject to procurement quantity

STD A A

Nomenclature: Launcher, Rocket Aircraft, 2.75 inch M200A1.

Description: The M200A1 is a 19-tube reparable 2.75 inch rocket launcher, used on the

UH1B/C/M, AH1G Aircraft. It is 60.6 inches long and weighs 139 lbs.

Remarks: TOE Authorization - not available this printing.

Basis of Issue: Approved BOI not available. For Planning Purposes!

2 each per UH1B/C/M equipped with Ml56 mount 3 each per AH-1 aircraft

Figure 2-17. Launcher, rocket aircraft, 2.75 inch M200A-1 (19-tube)

2-96

FM 101-20

2-21. UH-1D and H Armament Configurations.

// / '/

O ini

o

• DOOR MOUNTED WEAPONS ONLY

Figure 2-18. UH-ID and H Armament configurations,

2-97

FM 101*20

AV 000142

Figure 2-19. M23 Armament subsystem on UH-1D/H (Iroquois) helicopter

2-98

FM 101-20

:

! 'r~ r

Figure 2-20. M23 Armament subsystem in forward stowed position (front view)

2-99

FM 101-20


ARMAMENT SUBSYSTEM: M23 APPLICABLE AIRCRAFT - TYPE, MODEL, SERIES: Utility UH-1D/H AVERAGE PROCUREMENT PRICE: $4,282 TYPE CLASSIFICATION: Standard LOGISTIC CONTROL CODE: A

NOMENCLATURE: Armament subsystem, helicopter, door pintle mounted 7.62mm machine gun, M60D.

DESCRIPTION: The M23 armament subsystem consists of two 7.62mm, machine guns, M60D, and two mounts; one on each side of the aircraft in the doorways. The pintle post assembly is attached to a base tube assembly which is attached to hard points on the helicopter fuselage. The machine gun, which is a belt fed, gas operated, air-cooled automatic weapon, is attached to a pivot cradle on top of the pintle post. The base can be employed at either the right or left side, and the pedestal is designed for right or left installation. The machine gun installs on either right or left pintle mounts without adaptation, and is a modified machine gun, M60, with aircraft ring type sights, spade grips and an improved feed system. A rapid reloading capability is provided by a 550 round ammunition box attached to the weapon by a flexible chute. A canvas bag attaches to the right side of the receiver to catch links and ejected cartridges. Free traverse and elevation is allowed within fixed stop limits to prevent self-inflicted damage to the helicopter. The subsystem utilizes all standard 7.62mm ammunition.

CHARACTERISTICS: MAXIMUM EFFECTIVE RANGE: 1100 meters ELEVATION FORWARD: MUZZLE VELOCITY: RATE OF FIRE: TRAVERSE: EMPTY WGT: 173 lbs AMMUNITION: CAPACITY: TYPE: SIGHTING:

+3.5°, AFT +6.5° DEPRESSION -80° 2750 FPS 550 SPM 2° to 178° in Azimuth LOADED WGT:

550 rounds per gun Linked 7.62mm Aircraft ring type

210 lbs


AVUM AVIM and Depot TM 9-1005-262-14 TM 9-1005-262-24P TM 9-1005-262-24P Not Applicable


KIT NSN PUBLICATION NICP FUND REQUIREMENTS 1005-00-907-0720 TM 9-1090-2é>2-15 B14 DA ControUed


2-100

FM101-20

S-JSL

Figure 2-21. M56 Mine Disperser

2-101

FM 101-20

2-22. M56 Aircraft Mine Dispersing Subsystem.

ARMAMENT SUBSYSTEM: M56 APPLICABLE AIRCRAFT TYPE, MODEL, SERIES: AVERAGE PROCUREMENT PRICE : $ 10,640 TYPE CLASSIFICATION: Standard LOGISTIC CONTROL CODE: A

UH:1D/H

NOMENCLATURE: Mine dispersing subsystem, aircraft

DESCRIPTION: The M56 is a helicopter mine dispersing subsystem consisting of a US Air Force SUU-13 dispenser containing 40 mine canisters. Each canister contains two antitank mines and one XM198 mine ejection charge. A battery is installed in each mine just prior to flight. Firing of the subsystem is controlled by the aircraft crew. Quantity and interval of mine canister firing is controlled from the cockpit. The mines will arm only after both ejection and impact. The minimum altitude for dispensing is 100 feet.

CHARACTERISTICS: LENGTH. DIAMETER: EMPTY WEIGHT: LOADED WEIGHT: CAPACITY: SIGHTING:

90.4 inches 14.5 inches 117 lbs 660 lbs 40 mines None

MAINTENANCE AND SUPPLY: Maintenance Instruction: Repair parts: Special tools: Shop sets

Direct Support TM 9-1345-201-30 TM 9-1345-201-30 TM 9-1345-201-30 Not Applicable


Operational instructions contained in TM 9-1345-201-10-1

2-102

FM 101-20

2-23. XM230EI Armament Subsystem, Helicopter, Turret Mounted, 30mm, YM230 -

ARMAMENT SUBSYSTEM: XM230EI APPLICABLE AIRCRAFT - TYPE, MODEL, SERIES: YAH-64A AVERAGE PROCUREMENT PRICE: TBD TYPE CLASSIFICATION: Development LOGISTIC CONTROL CODE:

NOMENCLATURE: ARMAMENT SUBSYSTEM, HELICOPTER, TURRET MOUNTED, 30MM, XM230.

DESCRIPTION: Consists of .the following major components: 30mm Chain Gun, Turret, Ammunition Storage and Transfer Mechanism and Control System. The Gun System is a 30mm XM230EI Hughes Chain Gun which fires 30mm XM788/789 (ADEN/DEFA class) ammunition having a rate of fire of 725 + 25 RPM.The weapon with drive motor and recoil adapters attached weights 110 lbs. The Turret weight is 156 lbs.

CHARACTERISTICS:

Effective Range: 4000 Meters Elevation: +10° to-60° Muzzle Velocity: 805 MPS Rate of Fire: 725 + 25 RPM Traverse: ± 110° Empty Weight: 568 LBS. Ammuniton: 30mm XM788/789 and ADEN/DEFA class.ammo Capacity: 1215 Rounds Sighting: IHAD SS and TADS


Maintenance Instruction: Repair Parts: Special Tools: Shop Sets:

AVUM and AVIM Support TM9- TM9- TM9- TM9-


KIT NSN PUBLICATION N1CP FUND REQUIREMENTS

Operational instructions for subsystem can be found in TM55-

FM 101-20

2-24. HMMS Hellflre Modular Missile System.

ARMAMENT SUBSYSTEM: Hellfire APPLICABLE AIRCRAFT-TYPE, MODEL, SERIES: YAH-64A AVERAGE PROCUREMENT PRICE: TBD TYPE CLASSIFICATION: Development LOGISTIC CONTROL CODE:

NOMENCLATURE: Hellfire Modular Missile System (HMMS)

DESCRIPTION:

The Point Target System (PTS) for the YAH-64A is comprised of the Hellfire Modular Missile System (HMMS) (missiles and launchers), Hellfire MissUe Equipment (HME) (electronics and dedicated control panels), and associated multipuropse controls and dis- plays. This system can be used with any of three seeker heads: Laser, RF/IR, or IRIS. The YAH-64A carries eight Hellfire missiles for the primary mission and up to sixteen missiles in alternate configurations.

CHARACTERISTICS:

Effective Range: Missile Velocity: Rate Of Fire: As Selected By Pilot/Gunner Empty Weight: Missile Capacity: Ammo Type: Sighting:


Maintenance Instructions: AVUM and AVIM Support Repair Parts: TM 9- Special Tools: TM 9- Shop Sets: TM 9-


KIT NSN PUBLICATION NICP FUND REQUIREMENTS

Operational instructions for subsystem can be found in TM55-

2-104

2-25. Aircraft Armament Subsystems Ammunition.

7.62mm Cartridges*

MODEL DESIGNATION & TYPE STATUS PURPOSE

ROUNDS/ BOX

PACKAGING

TYPE BOX CU FT WEIGHT POUNDS

DOT CLASSIFICATION DODIC REMARKS

7.62mm Ball Linked 4/1 w/Tracer

STD Anti- Personnel & Training

200 Metal M19A1

0.45 19 Small Arms Ammo C1CQD1

1305-A131 For M60 Series Guns

7.62mm Ball Linked 4/1 w/Tracer


1500 Metal M548

1.30 120 Small Arms Ammo Cl CQD 1

1305-A165 Mini-Gun

NOTE: 1. Although other linked 7.62mm ammunition may be used with the above weapons, a basis of issue has not been established for other 7.62mm types or packs for Army aircraft application.

2. Only the primary DODIC is shown.

3. Although the two types of ammunition are interchangeable, the Mini-Gun type is preferred for its ease in loading and its quality features (polished brass, position of links, etc.).

* Reference TM 9-1305-200

Source: MUCOM (AMSMU-MS-IM)

Source: DRSAR-MAS-SS

FM

101-2

0

Aircraft Armament Subsystems Ammunition (CONT).

50 Caliber Cartridges*


ROUNDS/ BOX

PACKAGING

TYPE BOX CUFT WEIGHT POUNDS


.50 Caliber, 4 API Linked w/APIT

STD Anti- Personnel & Anti- Material

100 Metal M2A1

.45 37.5 Small Arms Ammo Cl CQD 1

1305-A577

.50 Caliber, 4 Ball Linked w/Tracer


100 Metal M2A1

.45 37.5 Small Arms Ammo Cl CQD 1

1305-A577

NOTE: AP1/APIT may also be linked 3 to 1 ratio and may also be issued for training. Only primary DODIC is shown.

* Reference TM 9-1305-200

FM

101-20

2-1

07

• • • • • 2-25. Aircraft Armament Subsystems Ammunition (CONT).

20mm Cartridges*


ROUNDS/ BOX

PACKAGING

TYPE BOX CU FT WEIGHT POUNDS


MS6A3HEI Linked 4/1 with M220 TPT

STD Anti- Personnel Light Anti- Materiel, Capable of Initiating Oil Fires

100 Metal M548

1.3 93 Ammo F/Cannon W/Expl. Proj. Cl A QD Cl 7

1305-A653 For Gun M19S Range to 3000 meters

M5SA2TP Linked

MS5A2 Linked 4/1 with M220 TPT

STD

STD

Target Practice

100 Metal MS48

1.30 93 Small Arms Ammo Cl C QD 1

1305-A926 For Gun M195 Range to 3000 meters

Target Practice' w/Tracer

100 Metal M548

1.30 93 Small Arms Ammo Cl C QD 1

1305-A896 For Gun Ml95 Range to 3000 meters

FM

101-20

2-1

08

2-25. Aircraft Armament Subsystems Ammunition (CONT).

40mm Cartridges*

MODEL DESIGNATION & TYPE

M383 HE

M384 HE

M385 Practice

M430 HE DP

XM677 Linked 1/3 HET M383

XM677 Linked 1/3 HET M384

STATUS

STD

PURPOSE

Anti- Personnel

STD

STD

STD

Develop- ment

Anti- Personnel

Practice (Solid Aluminum or Plastic Proj)

Anti- Personnel Anti- Materiel (Shaped Chg)

Anti- Personnel W/T racer

ROUNDS/ BOX

50 (all linked)

50 (all linked)

50 (all linked)

50 (aU linked)

PACKAGING

TYPE BOX

Wood

Wood

Wood

Wood

50 (linked 1 rd to every 3 M383/M384)

Wood

CU FT

1.2

1.2

1.2

1.2

1.2

WEIGHT POUNDS

53

53

DOT CLASSIFICATION

Ammo F/Cannon W/Expl. Proj. Dot Shipp. Cl A QD Cl 7


53

53

53

Ammo F/Cannon W/Inert Proj. Dot Shipp. Cl CQD Cl 1



DODIC

1310B571

1310 B572

1310 B470

1310 B576

1310 B480

1310 B542

1310 B529

1310B527

REMARKS

W/M16A2 link Ref. DTM 1310-221-12 (PA-AD-MB)

W/M 16 link

W/M16A1 link Ref. POMM 1310-204-12 (PA-DB7)

W/M 16 link

W/M16A1 link

W/M16A2 link Ref. DTM 1310-223-12 (PA-AD-MB)

Ref. DTM 1310-217-12 (PA-DB7)

XM683 HE

Develop- ment

Anti- Personnel (extended ranged RAP)

50 (all linked)

Wood 1.2 53 Ammo F/Cannon W/Expl. Proj. Dot Shipp. CIA QD Cl 7

1310 B471 Rocket Assisted Projectile Extended Range 3000 meters max. Ref. DTM 1310-220-12 (PA-DB7)

XM684 HE

Contin- gency

Anti- Personnel

50 (all linked)

Wood 1.2 53 Ammo F/Cannon W/Expl. Proj. Dot Shipp. Cl A QD Cl 7

1310 B573 VT Fuze W/M383 Proj. Body W/M16A2 link Ref. DTM 1310-218-12 (PA-DB7)

FM

101-2

0

2-1

09

• • • • • 2-25. Aircraft Armament Subsystems Ammuniton (CONT).

40mm Cartridges* (CONT).

NOTES: 1. All rds linked with M16A1 link unless otherwise specified.

2. Those rds linked with M16 link are for use Armament Subsystem using M75 Automatic Grenade Launcher. Those rds linked w/M16Al or M16A2 links are suitable for use in Armament Subsystem using the M75 or M129 Automatic Grenade Launcher.

Source: AARCOM (DRSAR-MAS-SS)

FM 101-20

2-110 2-26. Aircraft Armament Subsystems Rockets.

2.75 inch Rockets*

TYPE STDZN PURPOSE PACKAGING

RDS/Per Box Type CuFt Wt Lbs DOT

CLASS FSC & DODIC

REMARKS Wpn Lehr M158A1 M200A1

Rkt 2.75” Flech w/whd WDU-4A/A w/base fuze w/Mtr MK40

Rkt 2.75” HEAT w/whd MKS w/Fuze MK181 w/ Mtr MK40

Rkt 2.75” HE w/whd M229 w/Fuze M429 w/Mtr MK40

Rkt 2.75” HE w/whd M151 w/Fuze M429 w/ Mtr MK40


RktCMLAgt 2.75” SMK WP M156 w/Fuze M423 w/ Mtr MK40


Rkt 2.75” Practice WTU-l/B whd/slug w/ Mtr MK40

Rkt 2.75” Illumination w/whd M257 w/Fuze MBO w/Mtr MK40

Anti- Personnel

Armor Piercing Anti- Personnel

Anti- Personnel

Anti- Personnel

Anti- Personnel Anti- Materiel

Target Marking & Incendiary

Anti- Personnel Anti- Materiel

Practice & Training

Target Illumination

4 and 25

4 and 25

4 and 25

4 and 25

4 and 25

4 and 25

4 and 25

3 whds w/fuze, 3 Mtrs unassembled

Wood

Wood Wood

Wood Wood

Wood Wood

Wood Wood

Wood Wood

Wood Wood

Wood Wood

Wood

3.0 17.9

2.8 3.2

3.47 20.8

3.0 17.9

3.0 17.9

3.0 17.9

3.47 20.8

3.0 17.9

3.0

127 776

102 125

162 996

127 776

127 776

127 776

162 996

127 776

117

1340-H459

1340-H487

1340-H488

1340-H489

1340-H490

1340-H519

1340-H534

1340-H828

1340-T012

Same

Same

Same

Same

Same

Same

Same

Same

Same

FM 101-20

2-111

2-26. Aircraft Armament Subsystems Rockets (Cont).

2.75 inch Rockets*

TYPE

Rkt 2.75” Practice XM243 whd w/Fuze M435 w/Mtr MK40

Rkt 2.75” HEAT Whd M247 w/Fuze PIBD M438 w/Mtr MK40

Rkt 2.75” HE w/ Whd M229 w/Fuze XM433 w/Mtr MK40

Rkt 2.75” HE w/ Whd M151 w/Fuze XM433 w/Mtr MK40

Rkt 2.75” F lech w/ Whd XM255 w/Fuze RC XM439

STDZN

LP-T

PURPOSE

Training & Testing

Armor Piercing Anti- Personnel

Selectable Functioning f/Bunker Penetration & Anti- Personnel

Selectable Functioning f/Bunker Penetration & Anti- Personnel

Selectable Functioning Anti- Personnel Anti- Materiel

PACKAGING RDS/Per Box Type CuFt Wt Lbs

4 and 25

4 and 25

4 and 25

4 and 25

4 and 25

Wood Wood

Wood Wood

Wood Wood

Wood Wood

Wood Wood

3.47 20.8

3.47 20.8

3.47 20.8

3.0 17.9

3.0 17.9

162 996

147 886

162 996

127 776

127 776

DOT CLASS FSC & DOD1C

1340-H468

1340-H826 (will replace 1340-H487)

1340-H469

1340-H471

1340- (will replace 1340-H459)

REMARKS Wpn Lehr M158A1 M200A1

Same

Same

M200A1 Mod

M200A1 Mod

M200A1 Mod

Source: MIRADCOM (DRCPM-RK)

FM 101-20

FM 101-20

2-27. Aircraft Armor Systems.

Armor protection against enemy small arms fire is provided for Army aircraft crew and critical components. Types of crew protection include armored seat bottoms, side panels, and floor plates. Protection of critical components is provided by

means of armor for engine, fuel and oil accessories, and flight control items. The amount and place- ment of protective armor varies among different types of aircraft systems. The U-6, U-l, U-8, U-9 U-10, U-21, T-41, T-42, C-12 and UV-18 do not have1

armor. The backing for armor in the existing aircraft is mostly fiberglass. In the future fiberglass may be replaced by KEVLAR.

2-112 v

ro

2-27. Aircraft Armor Systems (Cont).

AIRCRAFT

AH-1G/S TH-1G

CH-47A

CH-47A/B/C

CH-47A/B

CH-47C

CH-54A

CH-54B

OH-6A

OH-58A

OH-58C

SYSTEM

Crew and component protection

Crew protection (Aerosmith seat)

Crew protection (Alsco seat)

Component protection

Component protection




Crew and component

protection

ARMOR WEIGHT

243 lb/acft

234 lb/acft

139 lb/acft

491 lb/acft

510 lb/acft

1164 lb/acft

1233 lb/acft

119 lb/acft

MATERIAL

B4C with Fiberglass Backing

AI2O3 with Fiberglass Backing

A12O3 with Fiberglass Backing

DPS and Fire Suppression Foam

DPS and Fire Suppression Foam

B4C with Fiberglass and DPS

B4C with Fiberglass and DPSA

112 lb/acft

B4C with Fiberglass Backing and DPS

PART NO. FSN

N/A - Furnished with aircraft and not available in kit form.

1560-CH47-225

1560-CH47-300

113550-3

113759-2

6407-75100-013

1680-912-3944

1680-947-9829

1560-945-4828

1680-073-8396


B4C with

Fiberglass Backing

UH-IB/C/D/9/M/V EH-1H, EH-1X

UH-1B/C/D/H/M/V EH-1H, EH-1X

UH-60A

Crew protection

Crew protection

Gunner protection

Crew protection

108 lb/acft

210 lb/acft

46 lb/acft

260 lb/acft

B 4 C with Fiberglass Backing

AI2O3 with

Aluminum Backing

AI2O3 with

Aluminum Backing

B 4 C with KEVLAR

1560-OH6-000-3 1560-133-8381

N/A - Furnished with acft and not

available in kit form.

NIA-

178061- 3 and

178062- 3

1560-UH1-350-1

N/

1560-725-6073 ✓

^ 1680-933-9384 and ^

^1680-933-9385

'/Í680-067-8208 J


CO

FM 101-20

2-114 2-27. Aircraft Armor Systems (Cont).

AIRCRAFT

OV-1 B/C '*

OV-1D

RV-1D

SYSTEM ARMOR WEIGHT

Crew protection consisting of combinations of:

(1) Nose armor, KA-60 camera provisions 63 lb/acft

(2) Nose armor, SLAR provisions 53 lb/acft (3) Nose armor, without KA-60 and SLAR

provisions 65 lb/acft (4) Side armor, homing antenna provisions

21 lb/acft (5) Side armor, without homing antenna

provisions 19 lb/acft (6) Side armor, side panel with circuit breaker

panel aft center right panel 24 lb/acft (7) Side armor, side panel without circuit

breaker panel 25 lb/acft

(8) Side armor, side panel common to all aircraft 68 lb/acft

(9) Extended side armor and floor

armor on OV-1C, 181 lb/acft

MATERIAL

AI2O3 with

Fiberglass Backing

PART NO.

1560-OV1-120-1 1560-OV1-121-1 1560-OV1-122-1

1560-OV1-123-1

1560-OV1-124-1

1560-OV1-125-1

1560-OV1-126-1

1560-OV1-127-1

1560-OV1-006-1

FSN

1560-947-3446 1560-947-3447 1560-947-3448

1560-947-3451

1560-947-3452

1560-947-3453

1560-947-3449

1560-947-3450

1560-943-0754

Provisions only for armor. When armor is added, its weight will be the same as OV-1C

AI2O3 with Fiberglass backing

See OV-1B/C See OV-1B/C

Provisions only for armor. When armor is added, its weight will be the same as OV-1B

AI2O3 with Fiberglass Backing

SeeOV-lB/C See 0V-1B/C

AI2O3 - Aluminum oxide composite armor B4C - Boron carbide composite armor

SiC - Silicon carbide DPS - Dual property steel armor

Source: TSARCOM (DRSTS-ME)

FM

101-2

0

FM 101-20

2-28. AH-1G/S and TH-1G Armor

a. The AH-1G/S and TH-1G aircraft are provided with aircrew and critical component armor. The pilot’s seat is made of dual hardness steel armor. The fixed side panels are made of a hard faced composite material. The entire passive defense system for the gunner is made of a hard faced composite material.

b. Critical component armor is located on each side of the engine to protect the engine compressor section and the fuel control unit. The standard fuel cells are self-sealing as follows: bottom 33% capacity against .50 caliber, center 33%capacity 30 caliber, and the top 34% is not self-sealing. The fuel crossover line is also self-sealing. The new crashworthy fuel cells are self-sealing against 20mm over their entire capacity. The fuel crossover line is self-sealing.

ENGINE AND TRANSMISSION OIL COOLER BY-PASS SYSTEM

- -

/ ,*•

• /

/ /

ENGINE FUEL CONTROL ✓ AND COMPRESSOR ARMOR '

\ y' / S'

, * ^

A

ARMOR STEEL PILOTS SEAT AND CERAMIC SIDE PANELS

CERAMIC GUNNERS SEAT AND SIDE PANELS

Figure 2-22 AH-1G/S and TH-1G Armor

2-115

FM 101-20

2-29. CH-47 Armor.

a. The CH-47 aircraft are provided with aircrew and critical component armor.

b. The aircrew armor material is aluminum oxide hard faced composite capable of defeating 30 caliber projectiles.

c. DPS armor has been provided for the following critical components:

(1) Armor for the fore and aft flight control actuators in four locations.

(2) Armor for the flight control closet.

(3) Armor for the fuel crossover valve.

(4) Fire, suppression foam on fore and aft faces of both fuel tanks.

t. SWIVELING ACTUATOR

PIVOTING ACTUATOR AFT ROTOR DUAL BOOST ACTUATORS

- >i HU — FORWARD

..— ROTOR DUAL *»

} ' YT''7

< /:■- nr-*» w—

\ : V * r f J fix ^ / fF(

V-

PIVOTING ACTUATOR

BOOST ACTUATORS I SWIVELING ACTUATOR-

'ï• FUEL CROSS OVER VALVE \—l / •' { X

FIRE SHEATHING

' V

\ *

•••

■>//. % l.

»• ci \ -•» y: \:. ■ \ > .. ..-y' r **■'

FLIGHT CONTROL CLOSET-

AV 000217

Figure 2-23. CH-47 Armor

2-116

FM 101-20

2-30. Armor for the Armed and Armored Chinook.

a. Armor for the armed and armored Chinook consists of aircrew and component armor. The pilot and copilot have been provided with a crash attentuating integral 30 caliber armor seat.

b. The total installed weight of the armor system is 2700 pounds. Armor is provided for the following critical components:

(1) Controls closet area of flight controls system.

(3) Copilot’s control box.

(4) Linkage from copilot’s controls to closet.

(5) Flight controls mix complex.

(6) Walking beam rod ends and bellcrank.

(7) Aft fuselage controls, rods, and bellcrank.

(8) Aft pylon controls, rods, and bellcrank.

(9) Accessory gear box, quill shaft.

(2) Swiveling and pivoting dual actuators in forward and aft pylons.

c. The armor material is dual property steel capable of defeating 50 caliber API projectiles.

2-117

FM 101-20

2-31. CH-54A Armor.

a. The CH-54A aircraft are equipped with aircrew and critical component armor. The pilot, copilot, and aft facing pilot are provided with armor placed on and around the existing seats. Protection is provided for the back, bottom, and sides. Frontal protection is via chest protector.

b. The 30 caliber armor material is primarily a boron carbide hard faced composite with dual hardness steel protecting the rod ends and bellcranks on the transmission deck. The weight of the armor for the pilot’s seat is 120 pounds, for the copilot’s seat is 111 pounds, and for the aft facing pilot’s seat is 86 pounds. Armor is provided for the following critical components:

(1) Servos, rod ends, and bellcranks under the pilot’s floor.

(2) Controls closet.

(3) External rod ends and bellcranks.

(4) Armored panel between the engine for separation purposes.

(5) Main servos.

(6) Primary hydraulic reservoir.

(7) Fuel tank sumps.

(8) Tail rotor servo control.

(9) Incorporation of a dual tail rotor control cable.

c. Total increase in aircraft weight is 1167 pounds.

TAIL ROTOR SERVO CONTROL

■ fj r— ENGIN!

í " p * 'v •VWffi A

MAIN SERVOS

ENGINE SEPARATION

PILOT, CO-PILOT AND AFT FACINC PILOT SEATS

f* PRIMARY HYDRAULIC

>3^

o ■ ' ÄV/.,''---- ROD ENDS & BELLCRANKS

DUAL TAIL ROTOR CONTROL CABLE

‘■j % jí FUEL TANK ? SUMPS

! C ).i '•■rjy

//C\ CONTROLS CLOSET-

* * J K'.-J/ SERVO ROD ENDS, BELLCRANKS

VSSri»

/ f

Figure 2-24.CH-54 Armor

2-118

FM 101-20

2-32. OH-6A Armor.

a. The passive protection system for the OH-6A aircraft consists of aircrew and critical component armor. The pilot and copilot is provided with armor placed on the existing seats. Protection is provided for the back, bottom, and sides. Frontal protection is via chest protector.

b. The armor material is a 30 caliber boron carbide hard faced composite except for the panel under the seat and the engine compressor panel which are of dual property steel.

c. The weight of the complete installed system is 130 pounds.

d. Armor is provided for the following critical components:

(1) Engine compressor.

(2) Self-sealing oil lines.

(3) Self-sealing fuel lines.

(4) Engine and transmission oil cooler bypass valves.

(5) Fuel control valve.

< \Jf \ ri

u

\

. rÿ'--- ,-'-<2.^'

rfy, /■>- 'V

PILOT ARMOR

V,/ V

>i •¿¿ku.'-K i

! / 1 v/r/r,

ib''W-

//y\

W-’l I ' r-l/j tyilKjSV- ^ / "CO-PILOT ARMOR

XJV-

' >' r ! ENGINE AND TRANSMISSION —BY-PASS SYSTEMS WITH

^ '-'SELF SEALING LINES AND TANKS

COMPRESSOR ARMOR

FUEL CONTROL ARMOR

^ 7 ^ s ' /

. ■ - / y/''

Figure 2-25. OH-6A armor

2-119

FM 101-20

2-33. UH-1 Series Armor.

a. The UH-1 series aircraft are equipped with aircrew armor for the pilot and copilot. The armor consists of an integrated armored seat. Protection is provided from the bottom, rear, and sides. Frontal protection is via chest protector.

b. The armor material is aluminum oxide hard faced composite capable of defeating 30 caliber projectiles.

c. The headguard is an armor panel which attaches to the back of the seats. The gunner’s seat armor, unit is a plate of armor material securely fastened to the crew seats in the UH-1. It is provided with a cushion for the crewman to sit on.

s '

s' At'' A; A-

. y ,.x'SAX (/M'ïA [/ \ ,/

x' AX' “ /••--. V \ As \ f\ / \ / I u'J/j \ \j .. /- J/A . ✓ '.

y./s't * " 1 ■ ' * \\ yjs ti/ X'Á' /A ñ A '-A /

ILOT RMORED SEAT // ... ►“

fy 'i //fe <y-

'ft*

* '1

ÍIÍ

/ i’ 11

U1 " \Y- /' t sf' I 1 / / > r-

As / •>

W.X A r. x

PILOT 40RED SEAT

1 ’ .0'

,Ae xy

0mm mmm»m m J “

Figure 2-26. UH-1 Armor

2-120

FM 101-20

2-34. OV-1 Armor.

a. The OV-1 aircraft are provided with aircrew and critical component armor. The aircrew armor is located on the nose bulkhead cockpit sides, floor, hatch, and forward windöws. This armor had to be mounted on the airframe since the ejection seat would not tolerate the weight.

b. The material used for aircrew armor is a 30 caliber aluminum oxide hard faced composite system. Critical component protection, which protects a

hydraulic valve in the landing gear system, is dual property steel armor.

c. Due to the various aircraft and avionic configurations, different armor sub-kits are required for any one model. All OV-1C aircraft require five of these sub-kits, while the OV-1B requires only four. The extended side and floor armor sub-kit provided for the OV-1C is not used on OV-JB aircraft due to weight and balance considerations. Consequently the armor systems for the OV-1C model aircraft weigh 360 pounds as opposed to 180 pounds for the OV-1B.

••• \

NOSE ARMOR -

; » ■ A 'f// l~t 1 XT!

lag V

OV-1 C& OV-1 D

EXTENDED ARMOR

SIDE ARMOR

•FLOOR ARMOR

A

V OV-1B & RV-1D

Figure 2-27. OV-1 Armor

FM 101-20

Section III. FERRYING AND SHIPPING

2-35. Surface Shipment.

Preparation of large numbers of aircraft for simultaneous mass movement by ocean transport had its inception in the latter part of June 1965.

Deployment of the 1st Cavalry Division (Airmobile) involved movement of a large number of aircraft, which was a first of this type and magnitude for the U. S. Army. Since the operation involved movement of approximately 500 aircraft, staging areas had to be established to receive, process, and marshall, in

accordance with the numbers designated fpr each of four vessels. Ports of loading were designated at Brookley Air Force Base, Mobile, Ala., and Mayport Naval Base, Jacksonville, Fla.

As a result of the experience with the 1st Cavalry Division deployment and other vessel shipments of aircraft to Southeast Asia, time/motion studies have provided input for developing the following table relating to processing Army aircraft for surface shipment.

i

1

I

(

Source: DRSTS-SDP

t

i

a' ¡V

2-122

2-123

2-36. Surface Shipment Processing Time. é

MAN HOURS (M/H) AND ELAPSED TIME (ET) MAN-HOURS ÀND ELAPSED TIME REFERENCED RQR TO PROCESS 1EA. FOR OVERSEAS SHIPMENT TO DEPROCESS 1 EA. PUBLICATION

Type of Aircraft

Top Deck Reusable Below Deck Top Deck Reusable Below Deck

M/H ET M/H ET M/H ET M/H ET

AH-1— CH-47 CH-54 OH-6A OH-58 UH-1— U-8D, RU-8 U21/RU21 OV-1 UH-60A—

122

24Í 48Í NA NA 12l 40 40 45 3

22

4 6 NA NA 22

5 5 5 3

18 NA NA 3 3 18 NA NA NA 3

3 NA NA 1 1 4 NA NA NA 3

61 12 2 TM55-1500-339S 18 3 NA NA TM1-CH47S 56 8 NA NA TM1-CH54S NA NA 3 1 TM1-OH6-S NA NA 3 1 TM55-1500-338S 6 1 12 2 TM55-1500-219S 48 6 NA NA TM1-U8-S 48 6 NA NA TM1-U21S 55 9 NA NA TM1-OV1-S 3 3 3 3 3

i Cover sets are not items to be requisitioned. Only CONUS and overseas outloading points preparing aircraft for movement are authorized to request cover sets.

c\

— Not recommended, covers should be used if placed on top deck.

— Not available, if information is needed contact DRSTS-SDP (2)

FM 101-20

2-124 2-37. Air Shipment Processing Time.

Aircraft

Type

Air Force

Aircraft

No. of Aircraft

Loaded Required Disassembly Disassembly Time

per Aircraft

M/H ET (Hrs)

Reassembly Time

per Aircraft

M/H ET (Hrs)

Referenced

Publications

AH-1

CH-47

CH-54

OH-6A

OH-58

C-5

C-141

C-130

C-5

C-5

C-5

C-141

C-130

C-5

12

15

3

Main rotor blades, stub wings, tail rotor blades,

synch elevators ejector tube assembly.

Same, plus Low Profile Skid

Main rotor blade & hub, mast & swash plate

assy, stub wings, tail rotor blades, fairing assys,

transmission cowling, antennas, ejector tube

assy synch elevators, landing skids.

Same, less synch elevators & landing skids.

Rotary wing blades forward cowling ring & fairing assys, forward transmission pkg, aft

pylon pkg.

Main rotor blades, tail rotor blades, stabilizer

assy, antennas & poles, main landing gear & support. Separate cockpit from fuselage at station 210.

8

14

24

180

26

6

3

13

22

Main rotor blades, horizontal stabilizer,

upper vertical stabilizer.

Same

Same

Main rotor blades, vertical stabilizer.

Same, plus “piggy-back” configuration.

6

6

1.5

3

4

4

12

15

36

TM55-1500-339-S

5

6

16 225 36

TM1-CH47-S

TM1-CH54-S

TM1-OH6-S

3

3

.5

1

6

6

2

6

3

3

1

3

TM55-1500-338S

Source: DRSTS-SDP • • • • # F

M 101-20

2-125

• • • « 2-37. Air Shipment Processing Time (Cont).

Aircraft Type

Air Force Aircraft

No. of Aircraft Loaded

,JC h’-1 RequiredDisassfemlilÿ f

Disassembly Time per Aircraft

M/H ET (Hrs)

Reassembly Time per Aircraft

M/H ET (Hrs)

Referenced Publications

OH-58 (Cont.)

C-141

C-130

8

4

Main rotor blades & hub & mast, vertical stabilizer.


Same, plus tail rotor blades.

7.5

3

3

1.5

1

1

10

6

6

UH-1 C.D, H,M,V

EH-1H EH-1X

C-5

C-141

C-130

11 (C, M)

1 or 2

3 (D,H)

1

2 (D, H)

Main rotor blades, stabilizer bar, synch elevators, antennas, hinged panels.


Main rotor blades, stabilizer bar, rotor head & mast assy, tail rotor blades, skid landing gear, antennas, rearview mirror, cargo suspension assy. .

Same, plus “side-saddle” configuration.

Same , „ .

Same, plus “side saddle” configuration.

12

16

24

18

26

32

.30

24

30

4

5

40

32

.40

TM55-1500-219S

UX-8/RU-8

U-21/ ' RU-21*

C-5

C-5

Wings 16 32

Wings 16' 32

TM2-U8-S

TM1-U21-S

♦Not practical due to disassembly requirements.

FM 101-20

BZ

l’Z

2-37. Air Shipment Processing Time (Cont).

Aircraft

Type

OV-1B, C, D*

T-42A*

UH-60A

Air Force

Aircraft

C-5

C-141

NA

C-5

C141

C130

No. of Aircraft

Loaded

NA

2

1

Required Disassembly

Engines, wings, horizontal stabilizer, outboard vertical stabilizers, drop tanks, flaps, antennas.

Same, plus propellers, center vertical

stabilizer, main & nose landing gears, air scoop, cowlings & fairings, aileron pushrods, tubing.

NA

* *

* *

Disassembly Time per Aircraft

M/H

305

402

NA

* *

* *

ET (Hrs)

38

50

NA

Reassembly Time per Aircraft

M/H

750

950

NA

ET (Hrs)

94

119

Referenced Publications

TM1-OV1-S

NVAL

•Not practical due to disassembly requirements. ••Information not available, if needed contact TSARCOM(DRSTS-SDP)(2). NOTE: Current U.S. Army manuals for air shipment are not always current with Air Force doctrine,

nor do they reference appropriate Military Airlift Command (MAC) regulations. Therefore, Computerized Air Planning Service (CAPS) at Langley Air Force Base or the nearest MAC command post should be asked to provide current policies.

'S

• • • ♦

FM 101-20

FM 101-20

2-38. Weight and Cube for Crated Shipment.

TYPE OF AIRCRAFT WEIGHT (LB)

CUBE (CU FT)

AH-1G AH-1S CH-47A CH-47B CH-47C CH-54A CH-54B OH-6A OH-5 8 A UH-1B UH-lC UH-1D UH-1H UH-1M TH-55A

U-8D U-8F U-8G U-10A U-21/RU-21

OV-1B OV-1C OV-1D T-41B T-42A

10,000 10,000

*

*

* *

*

«

5,000 10,409 10,610 12,500 13,937 10,610

«

* *

♦

NVAL

2800 2800

* * * * *

*

ß ,280 2.241 2.241 2,400

3,213 2.241

*

*

♦

*

NVAL

(*)Crating of aircraft not recommended

2-127

FM 101-20

Section IV. TOOLS*

: 2-39. Aircraft Shop Sets/Tool Kits/Tool Sets (Common). \

Aircraft special tools listing are not included in this manual. Refer to the Technical Publications listed in Chapter 1, Section IV (Standard Aircraft Characteristics).

2-40. Shop Sets.

NOMENCLATURE SM/SC

Shop set, aircraft maintenance, ground handling and servicing, SC 1730-99-CL-A01 Set A, direct support (Army)

(NSN-1730-00-999-6194) Shop set, aircraft maintenance, ground handling and servicing, SC 1730-99-CL-A02

Set B, direct support (Army)

(NSN 1730-00-999-6195) Shop set, aircraft maintenance, ground handling and servicing, SC 1730-99-CL-A03

Set C, general support (Army)

(NSN 1730-00-999-6193) Shop set, aircraft ground handling and servicing, airmobile, direct support SC 1730-99-CL-A04

maintenance. Battalion GHS (NSN 1730-00-900-8316)

Shop set, aircraft maintenance, fixed base, flaw detection. Set A, direct SC 4920-99-CL-A01 support

(NSN 4920-00-321-9353) Shop set, aircraft maintenance, fixed base, sheet metal, Set A, direct support SC 4920-99-CL-A02

(Army)

(NSN 4920-00-944-1005) Shop set, aircraft maintenance, fixed base, sheet metal, Set B, direct SC 4920-99-CL-A03

support (Army)

(NSN 4920-00-944-1006) Shop set, aircraft, maintenance, fixed base, sheet metal. Set C, general SC 4920-99-CL-A04

support (Army)

(NSN 4920-00-944-0996) Shop set, aircraft maintenance, fixed base, hydraulic, Set A, direct support SC 4920-99-CL-A05

(NSN 4920-00-321-9363) Shop set, aircraft maintenance, fixed base, hydraulic, Set B, direct support SC 4920-99-CL-A06

(NSN 4920-00-321-9364)

* Source: DRSTS-SLDT(l)

2-128

FM 101-20

+ 2-39. Shop Sets (Cont).

NOMENCLATURE

Shop set, aircraft maintenance, fixed base, hydraulic, Set C, general support

(NSN 4920-00-321-9373) Shop set, aircraft maintenance, fixed base, welding. Set A, direct support

(NSN 4920-00-321-9375) Shop set, aircraft maintenance, fixed base, welding, Set B, direct support

(NSN 4920-00-321-9376) Shop set, aircraft maintenance, fixed base, welding. Set C,general support

(Army) (NSN 4920-00-944-0785)

Shop set, aircraft maintenance, fixed base, tool crib, Set A, direct support

(NSN 4920-00-321-9397) Shop set, aircraft maintenance, fixed base, tool crib, Set B, direct support

(NSN 4920-00-321-9403) Shop set, aircraft maintenance, fixed base, tool crib, Set C, general support

(NSN 4920-00-321-9405) Shop set, aircraft maintenance, fixed base, electrical, Set A, direct support

(Army)

(NSN 4920-00-944-0761) Shop set, aircraft maintenance, fixed base, electrical, Set B, direct support

(Army)

(NSN 4920-00-944-0760) Shop set, aircraft maintenance, fixed base, electrical, Set C, general support

(Army)

(NSN 4920-00-944-0757) Shop set, aircraft maintenance, fixed base, flaw detection, Set B, direct

support

(NSN 4920-00-321-9410)

Shop set, aircraft maintenance, fixed base, flaw detection, Set C, general

support

(NSN 4920-00-321-9411) Shop set, aircraft maintenance, fixed base, paint, Set B, direct support

(Army)

(NSN 4920-00-944-0759) Shop set, aircraft maintenance, fixed base, paint, Set C, general support

(Army)

(NSN 4920-00-944-1007) Shop set, aircraft maintenance, fixed base, instrument, Set B, direct support

(NSN 4920-00-321-9416)

SM/SC wvt»,vy«.

SC 4920-99-CL-A07

SC 4920-99-CL-A08

SC 4920-99-CL-A09

SC 4920-99-CL-A10

SC 4920-99-CL-A11

SC 4920-99-CL-A12

SC 4920-99-CL-A13

SC 4920-99-CL-A14

SC 4920-99-CL-A15

SC 4920-99-CL-A16

SC 4920-99-CL-A17

SC 4920-99-CL-A18

SC 4920-99-CL-A19

SC 4920-99-CL-A20

SC 4920-99-CL-A21

2-129

FM 101-20

2-39. Shop Sets (Cont). »

NOMENCLATURE SM/SC

Shop set, aircraft maintenance, fixed base, instrument, Set C,general

support (Army)

(NSN 4920-00-944-0784)

Shop set, aircraft maintenance, fixed base, engine, Set B, direct support

(Army)

(NSN 4920-00-944-0884)

Shop set, aircraft maintenance, fixed base, engine, Set C, general support

(Army)

(NSN 4920-00-944-0786) Shop set, aircraft maintenance, fixed base, propeller and rotor, Set B, direct

support (Army)

(NSN 4920-00-944-1014) Shop set, aircraft maintenance, fixed base, propeller and rotor, Set C, general

support (Army)

(NSN 4920-00-944-1015) Shop set, aircraft maintenance, fixed base, power train, general support

(Army)

(NSN 4920-00-944-0838)

Shop set, aircraft maintenance, semitrailer mounted, A-l, tool crib, electrical,

flaw detection, direct support

(NSN 4920-00-621-2032)

Shop set, aircraft maintenance, semitrailer mounted, A-2, sheet metal, welding,

hydraulic, direct support

(NSN 4920-00-621-2033)

Shop set, aircraft maintenance, semitrailer mounted, B-l, tool crib and flaw

detection, direct support

(NSN 4920-00-621-2034) Shop set, aircraft maintenance, semitrailer and trailer mounted, B-2, electrical,

instrument, and hydraulic, direct support

(NSN 4920-00-621-2035)

Shop set, aircraft maintenance, semitrailer mounted, B-3, sheet metal and

welding, direct support

(NSN 4920-00-621-2036) Shop set, aircraft maintenance, semitrailer mounted, B-4, machine and

engine shop, direct support

(NSN 4920-00-621-2037)

SC 4920-99-CL-A22

SC 4920-99-CL-A23

SC 4920-99-CL-A24

SC 4920-99-CL-A25

[BK SC 4920-99-CL-A26

U

SC 4920-99;CL-A27 he ■ IB

SC 4920-99-CL-A28

SC 4920-99-CL-A29

SC 4920-99-CL-A30

SC 492U-99-CL-A31

SC 4920-99-CL-A32

SC 4920-99-CL-A33

• 2-130

FM 101-20

2-39. Shop Sets (Cont).

-\ NOMENCLATURE SM/SC

Shop set, aircraft maintenance, trailer mounted, B-6, paint shop, direct support

(NSN 4920-00-621-2038)

Shop set, aircraft maintenance, semitrailer mounted, C-l, tool crib, general support

(NSN 4920-00-621-2039) Shop séf? aircraft maintenance, semitrailer and trailer mounted, C-2,

electrical shop, general support (NSN 4920-00-621-2040)

Shop.set, aircraft maintenance, semitrailer mounted, C-3, flaw detection, general support

(NSN 4920-00-621-2041) Shop set-, aircraft maintenance, semitrailer mounted, C-4, sheet metal,

general support

(NSN 4920-00-621-2042) Shop^set? aircraft maintenance, semitrailer mounted, C-5, welding, general

support (NSN 4920-00-621-2043)

Shop set; aircraft maintenance, semitrailer mounted, C-6, machine shop,

general support (NSN 4920-00-621-2044)

Shop set, aircraft maintenance, semitrailer mounted, C-7, engine and hydraulic, general support

(NSN 4920-00-621-2045) Shop set, aircraft maintenance, semitrailer mounted, C-8, instrument shop,

general support

(NSN 4920-00-621-2046) Shop set, aircraft maintenance, trailer mounted, C-10, paint shop, general

support

(NSN 4920-00-621-2047) Shop set, aircraft maintenance, semitrailer mounted, B-5, propeller and rotor,

direct support

(NSN 4920-00-649-6509) Shop set, aircraft maintenance, semitrailer mounted, C-9, propeller and

rotor, general support

(NSN 4920-00-649-6509)

Shop set, aircraft maintenance, semitrailer mounted, C-l 1, power train, general support

(NSN 4920-00-649-6510)

SC 4920-99-CL-A34

SC 4920-99-CL-A35

SC 4920-99-CL-A36

SC 4920-99-CL-A37

SC 4920-99-CL-A38

SC 4920-99-CL-A39

SC 4920-99-CL-A40

SC 4920-99-CL-A41

SC 4920-99-CL-A42

SC 4920-99-CL-A43

SC 4920-99-CL-A44

SC 4920-99-CL-A45

SC 4920-99-CL-A46

2-131

FM 101-20


NOMENCLATURE SM/SC

Shop set, aircraft maintenance, airmobile, direct support section, airmobile

division

(NSN 4920-00-906-9727) Shop set, aircraft maintenance, airmobile, tool crib, direct support maintenance,

Battalion set No. 1

(NSN 4920-00-906-9728) Shop set, aircraft maintenance, airmobile, electrical, instrument,

hydraulic, direct support maintenance. Battalion set No. 2

(NSN 4920-00-906-9729) Shop set, aircraft maintenance, airmobile, sheet metal and welding,

direct support, Battalion set No. 3

(NSN 4920-00-906-9730) Shop set, aircraft maintenance, airmobile, machine and engine, ■

direct support maintenance. Battalion set No. 4 (NSN 4920-00-906-9731)

Shop set, aircraft maintenance, airmobile, propeller and rotor, direct support maintenance, Battalion set No. 5

(NSN 4920-00-906-9732) Shop set, aircraft maintenance, airmobile, flaw detection, direct

support maintenance, Battalion set No. 6 (NSN 4920-00-906-9733)

Shop set, aircraft maintenance, airmobile, company size, direct

support, CH-47

(NSN 4920-00-133-8157) Shop set aircraft maintenance, airmobile, company size, direct

support, CH-47/OH-6

(NSN 4920-00-133-8156) Shop set, aircraft maintenance, airmobile, company size, direct

support, UH-1

(NSN 4920-00-133-8154) Shop set, aircraft maintenance, airmobile, company size, direct

support, UH-1/OH-6

(NSN 4920-00-133-8158)

SC 4920-99-CL-A47

y-f

SC 4920-99¿CL-A48

¿a-' vi-

se 4920-9^qL-A49

ti .. .. I'i;-' .■

SC 4920-99.-CL-A50 V.4 - *

VSZVl, SC4920-9^jCL-A51

Vi-

se 4920-9%CL;A52

t ioec'. V&VL,

SC4920-99CL-A53

. SC 4920-99.-CLTA89

SC 4920-99-CL-A89

- .4«; V

SC 4920-99-CL-A89

SC 4920-99-CL-A89

2-132

FM 101-20


NOMENCLATURE SM/SC

Shop Sët, Aviation Intermediate Maintenance: electrical, instrument, airmobile (NSN 4920-00-165-1453)

Shop Set, Aviation Intermediate Maintenance: hydraulic, airmobile (NSN 4920-00-165-1454)

i ' ' o

Shbp Set, Aviation Intermediate Maintenance: machine shop, airmobile (NSN 4920-00-405-9279)

Shop Set, Aviation Intermediate Maintenance: power train, airmobile (NSN 4920-00-001-4132)

Shop^Set, Aviation Intermediate Maintenance: rotor, airmobile (NSN 4920-00-405-9270)

Shop‘Set, Aviation Intermediate Maintenance: sheet metal, airmobile (NSN 4920-00-166-5505)

Shop Sèt, Aviation Intermediate Maintenance: tool crib, airmobile (NSN 4920-00-472-4183)

Shop Set, Aviation Intermediate Maintenance: turbine engine, airmobile (NSN 4920-00-224-3684)

Shop Set, Aviation Intermediate Maintenance: welding, airmobile (NSN 4920-00-163-5093)

SC 4920-99-CL-A91

SC 4920-99-CL-A91

SC 4920-99-CL-A91

SC 4920-99-CL-A91

SC 4920-99-CL-A91

SC 4920-99-CL-A91

SC 4920-99-CL-A91

SC 4920-99-CL-A91

SC 4920-99-CL-A91

2-133

FM 101-20

2-40. Tool Kits.

NOMENCLATURE SM/SC

Tool kit, aircraft mechanic’s, general

(NSN 5180-00-323-4692) Tool kit, airframe repairer: Army aircraft

(NSN 5180-00-323-4876) Tool kit, hydraulic repairman’s, Army aircraft

(NSN 5180-00-323-4891) Tool kit, propeller and rotor repairman’s. Army aircraft

(NSN 5180-00-323-4909) Tool kit, instrument repairman’s. Army aircraft

(NSN 5180-00-323-4913) Tool kit, electrical repairman’s, Army aircraft

(NSN 5180-00-323-4915) Tool kit, power plant: Army aircraft

(NSN 5180-00-323-4944) Tool kit, aircraft inspection, technical

(NSN 5180-00-323-5114) Tool kit, trainer, flight simulator, set No. 1

(NSN 5180-00-859-0556) Tool kit. Army aircraft, crash investigation

(NSN 5180-00-903-1049) Tool kit, powertrain: Army aircraft

(NSN 5180-00-003-5267)

SC 5180-99-CL-A01

SC 5180-99-CL-A02

.-.v SC 5180-99£L-A03

JO.

SC 5180-99-CL-A05

SC 5180-99-CL-A06

SC 5180-99-CL-A07

SC 5180-99-CL-A09

SC 5180-99-CL-A10

SC 5180-99-CL-A11

SC 5180-99-CL-A13

2-41. Tool Sets.

NOMENCLATURE SM/SC

Tool Set, Aviation Unit Maintenance, Set No. 1: Airmobile (NSN 4920-00-159-8727)

Tool Set, Aviation Unit Maintenance, Set No. 1: Fixed Base (NSN 4920-00-504-9258)

SC 4920-99-CL-A90

SC 4920-99-CL-A90

Tool Set, Aviation Unit Maintenance, Reciprocating Engine Supplement (NSN 4920-00-159-8728)

Tool Set, Aviation Unit Maintenance: company size, Set No. 2, airmobile (NSN 4920-00-567-0476)

SC 4920-99-CL-A90

SC 4920-99-CL-A92

2-134

FM 101-20

Section V.

2-42. Aircraft Inspections.

This section is under a complete revision. Data will not be available until the 2nd quarter, FY 79. This data will be included in the next update to FM 101-20 Ih February 1980. Until this data is available, continue to use the inspection criteria in the Technical Publications listed in Chapter 1, Section IV, Standard Aircraft Characteristics.

-I'M

■

■ JD-Ç

1

Di

Source: DRSTS-MEN

INSPECTIONS

2-135

FM 101-20

Section VI. FUEL AND OIL

2-43. Fuel and Oil Costs. (FY 78)

TYPE

AIRCRAFT

FUEL

GRADE 1/

COST

PER

GAL 1/

OIL

MIL-L-

SPECIFI-

CATION U

COST

PER

QT 1/

AH-1G/S

CH-47A

CH-47B

CH-47C/D■••

CH-54A

CH-54B

OH-6A

OH-58A/C . . .

UH-1B/C ....

UH-1D

UH-1H/M/V. . EH-1H/EH-1X TH-55A

U-8D/RU-8D

U-8F

U-8G

U-10A

U-21A

RU-21A

RU-21B

RU-21C

JP-4/5

JP4

JP-4/5

JP-4/5

JP4/5

JP4/5

JP4/5

JP4

JP4/5

JP4/5

JP4

115/145

115/145

115/145

115/145

115/145

JP4/5

JP4/5

JP4/5

JP4/5

.436/.456

.436

.436/.4S6

.436/.456

.436/.456

.436/.456

.436

.436/.4S6

.436/.456

.436

.590

.590

.590

.590

.590

.436/.456

.436/.456

.436/.456

•436/.456

7808/23699

23699

23699

23699

23699

23699

23699

23699

23699

23699

23699

22851

22851

22851

22851

22851

23699

23699

23699

23699

2.26

2.26

2.26

2.26

2.26

2.26

2.26

2.26

2.26

2.26

2.26

.67

.67

.67

.67

.67

2.26

2.26

2.26

2.26

2-136

FM 101-20

2-43. Fuel and Oil Costs (Cont).

TYPE

AIRCRAFT

RU-21D

U-21G

RU-21E

U-21F

RU-21J RU-21H

OV-1B ......

OV-1C (w/L -15)

OV-1D

T-41B ......

T-42A

C-12A

UV-18A

UH-60A

YAH-64A

FUEL

GRADE y

JP-4/5

JP-4/5

JP4/5

JP-4/5

JP-4/5 JP-4/5 JP-4/5

JP-4/5

JP-4/5

115/145

115/145

JP-4/5

JP-4/5

JP-4/5

JP-4/5

COST

PER

. GAL 2/

.436/.456

.436/.456

.436/.456

.436/.456

.436/.4Ö6

.436/.4Ö6

.436/.456

.436/.456

.436/.456

.590

.590

.436/.456

.436/.4S6

.436/.4Ö6

.436/.456

OIL

MIL-L-

SPECIFI-

CATION J/

23699

23699

23699

23699

23699 23699 23699

23699

23699

26851

None

23699

23699

23699

23699

COST

PER

QT 3/

2.26

2.26

2.26

2.26

2.26 2.26 2.26

2.26

2.26

.83

.83 2.26

2.26

2.26

2.26

DATA S0URCE:-L/TB 55-9150-200-25, Engine and Transmission Oils, Fuels, and Additives for Army Aircraft.

2/ DFSC Price Bulletin No. 78-1 Standard Prices of Bulk Petroleum Items.

-2/ Federal Supply Catalog, C-ML-A, Army Management Data List, and Defense General Supply Center.

\ Note: The above costs are subj ect to frequent change and should be used for planning only. Next change will be Oct 1978.

Source: STSGP-FM AV 977-7247

I 2-137

2-138

2-44. Fuel and Oil Comsumption.

TYPE

OF

AIRCRAFT

NUMBER

OF

ENGINES

ENGINE

MODEL

DESIGN POWER PER ENGINE (SHP)

MAXIMUM NORMAL CRUISE1

DRIVE

TRAIN LIMIT SHP

FUEL CONSUMPTION

GAL PER AIRCRAFT HR

MAXIMUM NORMAL CRUISE

OIL

CONSUMPTION

QTSPER

AIRCRAFT HR

AH-1S 1 AH-1G/S 1 CH-47A 2

CH-47B 2

ÇH-47C 2

CH-54A 2

CH-54B 2

OH-6A

OH-58A/C UH-1B/C

UH-1D UH-1H/M/V

ËH-1H/EH-1X U-21A 2

RU-21A 2

RU-21B 2

RU-21C * 2

RU-21D 2

U-21G 2

RU-21H 2 U-21F 2

OV-1B 2

CV-1C 2

OV-1D 2

T53-L-703 T53-M3B

T55-L-7

T55-L-7C .

T55-L-11A

T73-P-1

T73-P-700

T63-A-5A/700 T63-700

T53-L-1 ID

T53-L-1 ID

T53-L-13B

T74-CP-700

T74-CP-700

T74-CP-702

T74-CP-702

T74-CP-700

T74-CP-700

T74-CP-700

PT6A-28

T53-L-7

T53-L-15

T53-L-701

1800 1400

2650

2850

3750

4500

4800

317

317

1100 1100 1400

550

550 750

750

550

550

550

680

1100 1150

1400

1400 1250

2200 2400

3000

4000

4430

270

270

900

900

1250

495

495 688

688 495

495

495

620

900

1000 1250

1050 937.5

1650.0

1800.0

2250.0

3000.0

3322.5

202.5

202.5

675.0

675.0

937.5

371.3

371.3

516.0

516.0

371.3

371.3

371.3

465.0

675.0

750.0

937.5

12903/ 1100 5200

5200

6000

5400

6600

250

317

1100 1100 1100

620 620

10924 101.5S 482.0

478.8

497.1

656.7

716.4

29.0

33.7

114.5

114.5

106.0

115.4

115.4 117.1 117.1

115.4

115.4

115.4 128.1

225.0 219.6

252.2

109.24) 101.551

407.8

442.0

497.1

656.7

716.4

29.0

29.1

96.5

96.5

106.0

107.0

107.0

117.1 117.1

107.0

107.0

107.0 117.1

190.1

198.5

232.8

100.84) S/93.I 305.9

331.5

372.8

555.22/

597. l2/

17.6

23.6

78.5

78.5

93.1

80.2

80.2 97.5 97.5

80.2

80.2 80.2

89.1

139.2

148.5

174.6

0.56 0.56

1.60

1.60

1.60

1.04

1.04

0.20 0.20 0.56

0.56

0.56

0.20

0.20 0.20 0.20

0.20 0.20 0.20 0.20

1.12 1.12 1.12

]_/ Cruise = 75% Normal

5/ Hog Mission 2.000 Ft. Pressure Altitude 9.000 Lbs. Gross Weight

2/ Based on 75%

Drive Train Limit

3/ 30 Min. 4/ Eight Tow Missiles

2.000 Ft. Pressure Altitude

9.000 Lbs. Gross Weight

• t

FM 101-20

2-139

2-44. Fuel, and OH Consumption (Cont).

>\|Hr

TYPE

OF

AIRCRAFT

NUMBER

OF

ENGINES

ENGINE

MODEL

DESIGN

POWER PER ENGINE (BHP)

MAXIMUM NORMAL CRUISE1

FUEL CONSUMPTION-“

GAL PER AIRCRAFT HR

MAXIMUM NORMAL CRUISE

. OIL- ■ ;

CONSUMPTION

QTSPER

AIRCRAFT HR

TH-55 '

U-8D/RU-8D

U-8F

U-8G

U'-TOA

T-41B

T-42A

C-12A UV-18A ÜH-60A

1

2 2 2 1 1 2 2 2 2

HI0-360-B1 A

.0-480-1 B

0-480-3 A

0-480-1 B

GO-480-G 1D6

IO-360-D

IO-470-L

PT-6-38

GE700T-700

180

340

340

■ 340

340

210 260

2*750

2] 920

160

320

320

320

320

210

260

120.0 240.0

240.0

240.0

240.0

157.5

195.0

750.0

15.1

57.0

60.5

57.0

30.2

15.5

39.2

115.4

13.4

53.6

56.8

53.6

28.4

15.5

39.2

107.0

10.1 40.2

42.6

40.2

20.1 1 1.6

29.4

80.2

0.17

0.50

0.50

0.50

0.25

0.25

0.50

0.20

NOTE: Aircraft in development or type classified contingency not included YAH-64A 2 GE700T-700 920 — 750.0

1/Cruise = 75% Normal

2) Shaft Horsepower -

Source: DARCOM PM’S TSARCOM RPO’S and PM’S

FM 101-20

THIS PAGE LEFT BLANK INTENTIONALLY.

2-140

FM 101-20

Section VII. MAINTENANCE MAN-HOURS

2-45. Total Direct Maintenance Man-Hours per Flight Hour (Combat).

TYPE AIRCRAFT

AVIATION UNIT MAINTENANCE (AVUM) ly

AVIATION INTERMEDIATE MAINTENANCE (AV1M) 2/ TOTAL

AH-1G/S

CH-47A

CH-47B

CH-47C

CH-54

OH-6A

OH-58A/C

UH-1B/C/M

UH-1D/H

OV-1C/D T-41B OV-1C

U-21/RU21 UH-60A

4.05

13.80

12.48

13.46

16.21

2.84

2.84

3.61

3.38

5.16 2.93 5.34

4.02 2.27

1.38

5.35

4.26

6.10

3.89

1.01

1.01

1.47

1^28

1.40 1.78 1.56

1.11 0.94

5.43

19.15

16.74

19.56

20.10

3.85

3.85

5.08

4.66

6.56 4.71 6.90

5.13 3.21

y AVUM is that organizational and integrated Direct Support Maintenance performed in company sized aviation units.

2/ AVIM is the amalgamation of direct and general support aviation maintenance units into a single maintenance unit performing both direct and general support aircraft maintenance.

NOTE: The above factors are direct man-hours only and are based on TOE Manpower Authorization Criteria (MACRIT).

Avionics and weapons systems are not included.

REFERENCE: AR 570-2 w/change 10

Source: DRSTS-MPM

2-141

FM 101-20

2-46. Manpower Authorization Criteria (MACRIT).

AIRCRAFT MAINTENANCE AND

TECHNICAL INSPECTION OPERATIONS

(MOS 67/68 SERIES)

AIRCRAFT MAINTENANCE AND

TECHNICAL INSPECTION OPERATION (MOS 67/68 SERIES)

1. Productive man-Hours. Ref AR570-2

2. Authorization formula and criteria.

a. Aviation Unit Maintenance (AVUM).

(1) Density of Aircraft MACRIT Factor Number Positions by Type X by MOS = Authorized

(1 to 9 Aircraft Category 1) USE 'TABLE I ONLY - MOS 67 Series

(2) Density of Aircraft MACRIT Factor Number Positions by Type x by MOS = Authorized

( 10 or more aircraft Category I) USE TABLES I AND la - MOS 67/68 Series

(3) Density of Aircraft MACRIT Factor Number Positions by Type x by MOS = Authorized

(1 to 9 Aircraft Category II) USE TABLE II ONLY - MOS 67 Series

(4) Density of Aircraft MACRIT Factor Number Positions by Type X by MOS = Authorzied

(10 or more Aircraft Category II) USE TABLES II AND Ha - MOS 67/68 Series

b. Aviation Intermediate Maintenance ( AVIM).

Density of Aircraft MACRIT Factor Number Positions by Type x by MOS = Authorized

(Table III Category II) (MOS 67 and 68 Series)

3. For force developers who utilize Annual Available Productive Man-hour (AAPMH) other than those listed in paragraph 2-7b(3). AR570-2 and/or Flying Hours as listed in Table IV. Column A below, substitute appropriate AAPMH and/or Flying Hours requirements in the following authorization formulae and criteria.

a. Aircraft Repairer (with FLYING CREWCHIEF) (MOS 67 Series).

STEP 1: Maintenance man-hours/ flight hour (Table V)

Annual flying hours (Table IV) or other source 2

.50 Annual Available 1 productive man-hours by category or other source 3

STEP 2: Density of Aircraft by Type

MACRIT Factor (From Step 1 above)

Number Positions plus Number Positions plus one Crewchief per Aircraft

Annual Available productive man-hours by category MACRIT or other _ Factor source 3 by MOS

2-142.

FM 101-20

b. AVUM: Aircraft Repairer without crewchiefs (MOS 67 Series).®

Density of Aircraft by Type

Maintenance man-hours/ flight hour (Table V)

Annual flying hours (Table I\0 or other source2

c. AVUM: Aircraft Component Repairer (MOS 68 Series).

Maintenance X man-hours/ X

Density4 of Aircraft by type

Maintenance man-hours/ flight hour (Table VI)

Annual flying hours (Table iyj or other source^

d. AVIM: Aircraft & Aircraft Component Repair (MÓS 67 &68 Series).


Density of Aircraft by type

Maintenance man-hours/ flight hour (Table VI)

Annual flying hours (Table I'VO or other source^

e. TECHNICAL INSPECTORS: (MOS 67 Series only).



Maintenance man-hours/ flight hour (Table VII)

Annual flying hours (Table IYJ or other source^

Annual Available productive man-hours by category or other source3




Number Positions Authorized



Number Positions ' Authorized

NOTE 1 NOTE 2 NOTE 3 NOTE 4 NOTE 5

Flying crewchiefs are 36 percent productive directive/non-flying crewchiefs are 50 percent projective direct Use the flying hours listed in Table IV (Column B) or those documented flight hours necessary to accomplish the mission. Substitutions may be made when the AAPMH figures vary from those listed in paragraph 2-7b(3), AR670-2 Only those units with 10 or more aircraft will be authorized MOS 68 Series. Aircraft OV-1B/C/D, UH-21 A, OH-6A, OH-58A, and AH-1G/S are not authorized flying crew chief. Nonflying crew chief’s positions may be designated from within the authorized position computation.

SAMPLE COMPUTATIONS (For units flying hours and/or AAPMH other than those in this regulation, see paragraph 3 above).

1. AVUM: Aircraft Repairer (with FLYING CREWCHIEF) (MOS 67 Series).

ASSUME 13 UH-1H, annual flying hours = 100; and 2300 AAPMH.

STEP 1: Maintenance man-hours/ flight hour (TableV)

4.12

X

X

Annual flying hours (Table IV) or other source^

1000

.50 Annual Available productive man-hours by catôry or other

__ source0,

1150

Annual Available productive man-hours by category or other = MACRIT source3 FACTOR 2300 = 1.29

STEP 2: Density of Aircraft by Type

13

X

X

MACRIT Factor Number One Crewchief by MOS = Positions _j_ per Aircraft =

1.29 = 16.77 13

Total (67N) Positions Authorized

= 29.97 or30

2. AVUM: Aircraft Repairer (without crewchief) (MOS 67 Series).

ASSUME 17 AH-1S, annual flying hbtirs = 500 and 2600 AAPMH.


17

Maintenance- man-hours/ flight hour (Table V)

4.93

Annual flying hours (Table IV/j

Annual Available productive man-hours

or other source2 ~ by category or other source3

500 2j>00

Number (67Y) Positions Authorized 16.11 or 16

3. Aircraft Component Repairer Computation for AVIM and AVUM (with 10 or more aircraft) are the same as SAMPLE COMPU- TATION 2, above.

2-143

FM 101-20

LIN A30221

AIRCRAFT OV-1B

AIRPLANE REPAIRER (67G) 1.76

UTILITY HELICOPTER REPAIRER (67N)

MEDIUM CARGO HELICOPTER REPAIRER (67U>

OBSERVATION HELICOPTER REPAIRER(67V)

HEAVY CARGO HELICOPTER REPAIRER (67X)

ATTACK HELICOPTER REPAIRER (67Y)

AIRPLANE INSPECTOR (Ô7G) 21

UTILITY HELICOPTER INSPECTOR (67N)

MEDIUM CARGO HELICOPTER INSPECTOR (67U)..

OBSERVATION HELICOPTER INSPECTOR (67V|

HEAVY CARGO HELICOPTER INSPECTOR (67X1

ATTACK HELICOPTER INSPECTOR I67Y)

MACRIT FACTORS

AVIATION UNIT MAINTENANCE (AVUM)

TABLE I (MOS 67 SERIES) Category 1 Unit (2600 AAPMH)

A30271 A30946 K317491 K317861 K303781 K303831 K304491 K30645 A30296 K31767 K31796

K31804 OV-lC/D U-21A UH-1B/C/M UH-1D/H CH-47A CH-47B CH-47C OH-6A OH-68A CH-64A/BAH-1G/S

K31042 K30515* K29660 K30616 K29694

1.66 1.78

.20

NOTE 1: 1NCLUDESONE FLYING CREWCHIEF PER AIRCRAFT. NOTE 2: IN UNITS WITH 10 OR MORE AIRCRAFT, FOR POSITIONS NOT JUSTIFIED BY MACRIT BUT ESSENTIAL FOR THE OPERATION OF THE UNIT. A TRADE

OFF IS AUTHORIZED AS LONG AS TOTAL AUTHORIZATION FOR POSITIONS IS NOT EXCEEDED.

AIRCRAFT POWERPLANT REPAIRER (68B) 06

AIRCRAFT POWERTRAIN REPAIRER (68D) .02

AIRCRAFT ELECTRICIAN (68F) .04

AIRCRAFT STRUCTURAL REPAIRER (68G) 12

AIRCRAFT PNEUDRAULICS REPAIRER (68H) .02

TABLE la(MOS 68 SERIES) Category I Unit (2600 AAPMH)

.04 0 2 06 .07

.02 .02

02 04

.12 12

.04 .02

.06 .06

01 .02

.06 .07

01 .02

.11 .10

32 .24

.11 10

.11 .10

.11 .06

.37 .06

.11 03

.16 09

.03 09

.04 .10

01 .09

.16 .06

07

.07

.02

.06

.02

LIN

MACRIT FACTORS'

AVIATION UNIT MAINTENANCE IAVUM)

TABLE II (MOS 67 SERIES)

Category II Unit(2700 AAPMH)

Q!

. K31767 K31804

OV-IOD U-21A UH-1B/G/M UH-lD/H CH-47A CH-47B CH-47C OH-6A OH-68A CH-64A/B AH lG/S

1.71 1.66

A30221 A30271 A30946 K317491 K317S61 K303781 K303831 K304491 K30646 K31042 A30296 . K31767 K31796

K31804 AIRCRAFT OV-1B

AIRPLANE REPAIRER (67G) 1.82

UTILITY HELICOPTER REPAIRER (67N) 1.56 1.95

MEDIUM CARGO HELICOPTER REPAIRER (67U) 4.82 4.46 4.63

OBSERVATION HELICOPTER REPAIRER(67V| 100 100


ATTACK HELICOPTER REPAIRER |67Y|

AIRPLANE INSPECTOR (67G) 19 .19 .17

UTILITY HELICOPTER INSPECTOR (67N) 16 .25

MEDIUM CARGO HELICOPTER INSPECTOR (67U) 73 .73 .73

OBSERVATION HELICOPTER INSPECTOR (67V) .15

HEAVY CARGO HELICOPTER INSPECTOR (67X)

ATTACK HELICOPTER INSPECTOR (67Y)

K30516 K30516

K29660 K29694

NOTE 1: INCLUDES ONE FLYING CREWCHIEF PER AIRCRAFT. NOTE 2: IN UNITS WITH 10 OR MORE AIRCRAFT, FOR POSITIONS NOT JUSTIFIED BY MACRIT BUT ESSENTIAL FOR THE OPERATION OF THE UNIT. A TRADE-

OFF IS AUTHORIZED AS LONG AS TOTAL AUTHORIZATION FOR POSITIONS IS NOT EXCEEDED.

AIRCRAFT POWERPLANT REPAIRER (68B) .06



AIRCRAFT STRUCTURAL REPAIRER I68G) .11


TABLE Ha (MOS 68 SERIES) Category II Unit <2700 AAPMH)

.04 .02 .05 07

02 02

.02 04

.12 .11

.04 .02

.05 06

.01 .01

.05 07

.01 .01

10 .09

30 22

10 09

.10 .09

.05 .03 '

10 .05 . i

.34 06

.10 .03

.14 .08

.05 NONE

.03 .09

.04 .09

01 .09

14 .04

06

07

02

.05

02

2-144

FM 101-20

MACRIT FACTORS1

AVIATION INTERMEDIATE MAINTENANCE (AVIM)

TABLE III Category II Unit (2700 AAPMH)

LIN

AIRCRAFT

A30221

OV-1B OV

A30271 A30946 K31749 K31766 K30378 K30383 K30449 K30645 K31042 K30616 K29660 A30296 K31767 K31796 K30516 K29694

K31804 1C/D U-21A UH-1B/C/M UH1D/H CH-47A CH-47B CH-47C OH-61 OH-58A CH &4A/B AH1G/S

AIRPLANE REPAIRER (07G) 26

UTILITY HELICOPTER REPAIRER(67N)

MEDIUM CARGO HELICOPTER REPAIRER (67U)

OBSERVATION HELICOPTER REPAIRER (67V)


ATTACK HELICOPTER REPAIRER (67X)

AIRCRAFT POWERPLANT REPAIRER (68B) .06



AIRCRAFT STRUCTURAL REPAIRER (68G) .17


29 .27

, 26

.78

.04

.04

.06

.10

.02

.09

.06

.01

.09

.01

24 .24

10

08

01

11

01

.29

.27

.12

.19

.08.

35

29

09

24

09

.03

.06

.01

.08

None

.17

.03

.01

.12

.01

54

.10

.06

.14

.13

.08

..27

.09

.08

.02

.09

.01

AIRPLANE INSPECTOR (67G 05 .05 .03

UTILITY HELICOPTER INSPECTOR (67N) 07 .07

MEDIUM CARGO HELICOPTER INSPECTOR (67U) I« .16 .16

OBSERVATION HELICOPTER INSPECTOR (67V) 03 .03

HEAVY CARGO HELICOPTER INSPECTOR (67X) 10

ATTACK HELICOPTER (67X) 1 05

NOTE 1: FOR POSITIONS NOT JUSTIFIED BY MACRIT, BUT ESSENTIAL FOR THE OPERATION OF THE UNIT, A TRADE-OFF IS AUTHORIZED AS LONG AS TOTAL AUTHORIZATION FOR POSITIONS IS NOT EXCEEDED.

LIN

K29660

K29694

K30378 K30383 K30499

K31749 D31767 K31804

K31786

K31795

K30515

K30616

K30646

K31042

A30221 A30271 A30296

A30946

TABLE IV FLYING HOURS DA APPROVED FLYING HOUR FACTORS

COLUMNA

AIRCRAFT

AH-1G/S

CH-47A/B/C

UH-1B/C/M

UH1D/H

CH-54A/B

OH-61

OH-68A

OV-1B/C/D

U-21A

TOE ACTIVE COMBAT ENVIRONMENT HOURS PER:

MONTH

65

58

66

79

43

68

68

68

74

YEAR

780

696

660

816

816

696

888

Column B INDIRECT SUPPORT

AIRCRAFT HOUR PER:

MONTH

26

26

26

26

36

YEAR

300

300

300

300

300

300

420

NOTE: Indirect support flying hours, Column B above, are applicable to those units (excluding divisional units) that are not directly or titally relatable to combat operations. Applicable to MTOE when directed by the M ACOM

2-145

FM 101-20

2-47. Aviation Intermediate Maintenance (AVIM) Support Units.

UNIT Productive Maintenance Man-Hours Per Year (Based on 2700 Hr Production/Man/Year)

TOE 55-89 Transportation Aircraft Maintenance Company Combat Aviation Battalion Airborne Division (or) Infantry Division

91,800 Aircraft Component Repair 141,700 Aircraft Repair 97.200 Aircraft Missile Systems Repetir 32,400 Aircraft Weapons Systems Repair 16.200 Avionics Repair

TOE 55-407 Transportation Aircraft Maintenance Company Transportation Aircraft Maintenance Battalion Airmobile Division

129,600 Aircraft Component Repair 178,200 Aircraft Repair 24,300 Aircraft Armament Repair 10,800 Aircraft Fire Control Repair 86,400 Avionics Repair

TOE 55-417 Transportation Aircraft Maintenance Company Support Battalion Air Cavalry Combat Brigade

170,100 Aircraft Component Repair 243,000 Aircraft Repair

54,000 Aircraft Fire Control Repair 18,900 Avionics Repair

TOE 55-424 Transportation Aircraft Maintenance Company Combat Aviation Battalion Armored Division (or) Infantry Division (Mech)

75,600 Aircraft Component Repair 110,700 Aircraft Repair 91,800 Aircraft Missile System Repair 16,200 Aircraft Weapons System Repair 13,500 Avionics Repair

♦TOE 55-457 Transportation Aircraft Direct Support Company

91,800 Aircraft Component Repair 121,500 Aircraft Repair 27,000 Aircraft Armament Repair 16,200 Aircraft Fire Control Repair 75,600 Avionics Repair

♦TOE 55-458 Transporation Aircraft General Support Company

140,400 Aircraft Component Repair 197,100 Aircraft Repair

16,200 Aircraft Armament Repair 8,100 Aircraft Fire Control Repair

118,800 Avionics Repair

TOE 55-459 Transportation Aircraft Intermediate Maintenance Support Company

TOE 55-459

TOE 55-459

Heavy Helicopter (CH-54) Section (Augmentation)

Fixed Wing (OV-l/U-21) Section (Augmentation)

205,200 Aircraft Component Repair 145,800 Aircraft Repair 29,700 Aircraft Armament Repair 18.900 Aircraft Fire Control Repair 72.900 Avionics Repair

8,100 Aircraft Component Repair 16.200 Aircraft Repair

16.200 Aircraft Component Repair 24,300 Aircraft Repair

2-146

FM 101-20

2-47. Aviation Intermediate Maintenance (AVIM) Support Units (Cont).

UNIT

TOE 55-459 Heavy Helicopter Fixed Wing Avionics Section (Augmentation)

Productive Maintenance Man-Hours Per Year (Based on 2700 Hr Production/Man/Y ear)

45,900 Avionics Repair

*To be replaced by TOE 55-459

Source: TSARCOM (DRSTS-SPME)

2-147

FM 101-20

Section VMI. MAINTENANCE CATEGORIES

2-48. The Three Categories of Maintenance are:

a. Aviation Unit Maintenance (AVUM):

This level includes all of the original organizational maintenance tasks plus some of the prior direct support maintenance tasks. It is that maintenance which is organic to the operating unit.

b. Aviation Intermediate Maintenance (AVIM):

This level of maintenance combines the remaining portions of capability of the prior direct and general support maintenance, thereby establishing a single level of support between AVUM and the depot.

2-148

FM 101-20

c. Aviation Overhaul Maintenance (Depot):

This level of maintenance provides for the repair/ overhaul of materiel beyond the capability of AVUM/ AVIM.

Reference AR 750-1.

NOTE: The three level maintenance concept replaces the previous four level maintenance categories of organization, direct support, general support and depot.

2-49. Installations with Capabilities to Perform Aviation Overhaul Maintenance-

Army Depot Location Typ® Acft

Corpus Christi

New Cumberland

Corpus Christi, Texas

Harrisburg, PA.

AH-1 Series UH-1 Series

0H-58A/C

U-8 Series CH-47 Series

CH-54A/B OH-1A

OH-58A/C

NOTE: Aircraft not maintained at CCAD and NCAD are contractor supported with commercial manuals.

Source: DRSTS-MPP

2-149

FM 101-20

OH-6A

67V 68B 68D 68F 68G

AVUM

1,901.28 89.76

114.24 48.96

163.20

AVIM

465.12 65.28

106.08 24.48

163.20

OH-58A

67V 68B 68D 68F 68G 68H

1,876.80 48.96 73.44 24.48

277.44 16.32

UH-1B/C/M

67N 68B 68D 68F 68G 68H

2,046,00 92.40 99.00 26.40 92.40 26.40

465.11 326.40

48.96 24.48

236.64 16.32 -I.

495.00 165.00 105.60 19.80

171.60 13.20

UH-1D/H

67N 68B 68D 68F 68G 68H

2,787.12 132.72 94.80 28.44

132.72 28.44

616.20 189.60 151.68 28.44

218.04 9.48

OV-1B

67G 68B 68D 68F 68G 68H

3,125.04 104.40 41.72 69.60

215.76 34.80

508.08 104.40

13.92 6.96

334.08 6.96

OV-1C/D

67G 68B 68D 68F 68G 68H

3,306.00 76.56 34.80 41.72

222.72 76.56

556.80 118.32

13.92 20.88

361.92 13.92

2-150

FM 101-20

TECHNICAL INSPECTORS

AH;1G/S 67Y3

UH-1B/C/M 67N3

UH-1D/H •67N3

OH-6A 67V3

OH-58A 67V3

CH-47A/B/C 67U3

CH-54A/B 67X3

U-21 67G3

OV-1B/C/D 67G3

AVUM 358.80

310.20

483,48

285.60

285.60

1,412.88

1,135.20

328.56

368.88

AVIM 93.60

132.00

142.20

65.28

65.28

313.20

196.08

53.28

97.44

2-151

FM 101-20

OH-6A(67V)

CAT I 1,901.28 x 1.4 = 2,661.79 ^ 2.500 = 1.06 CAT II 1,901.28 x 1.4 = 2,661.79 f 2,700 = .99

OH-58A (67V)

CAT I 1,876.78 x 1.4 = 2,627.52 i 2,500 = 1.05 CAT II 1,876.78 x 1.4 = 2,627.52 ¿ 2,700 = .97

UH-1D/H w/flying crew chief

CAT 1 2,787.12 x 1.4 = 3,901.97 -1,250 = 2,651.97 f 2,500 =1.06 + 1 = 2.06

CAT II 2,787.12 x 1.4 = 3,901.97 -1,350 = 2,551.97 f 2,700 = .95+1 = 1.95

UH-1B/C/M w/ flying crew chief

CAT I 2,046.0 x 1.4 = 2,864.4 -1,250 = 1,614.4 f 2,500 = .65 + 1 = 1.65

CAT II 2,046.0 x 1.4 = 2,864.4 -1,350 = 1,514.4 Í 2,700 = .56 + 1 = 1.56

OV-1B (67G)

CAT I 3,125.05 x 1.4 = 4,375.06 ¿ 2,500 = 1.75 CAT II 3,125.04 x 1.4 = 4,375.06 i 2,700 = 1.62

OV-1C/D (67G)

CAT I 3,306.0 x 1.4 = 4,628.4+ 2,500 = 1,85 CAT II 3,306.0 x 1.4 = 4,628.4 T 2,700 = 1.71

U-21 (67G)

CAT I 3,179.04 x 1.4 = 4,450.66 i 2,500 = 1.78 CAT II 3,179.04 x 1.4 = 4,450.66 i 2,700 = 1.65

2-152

FM 101-20

# 2,600 2,700

fe 68D 68F 68G 68H

OH-58A 48.96X1.4= 68.54 73.44X1.4 = 102.82 24.48X1.4 = 34.27

277.44X1.4 = 388.42 16.32X1.4 = 22.85

.03

.04

.01

.16

.01

.03

.04

.01

.14

.01

68B 68D 68F 68G 68H

UH-1B/C/M

92.40X1.4 = 129.36 99.00X1.4 = 138.60 26.40X1.4= 36.96 92.40X1.4 = 129.36 26.40X1.4 = 36.96

.05

.06

.01

.05

.01

.05

.05

.01

.05

.01

UH-1D/H

68B 68D 68F 68G 68H

132.72 X 1.4 94.80X1.4 28.44 X 1.4

132.72X1.4 28.44 X 1.4

185.81 132.72 39.82

185.81 39.82

^^8

68B 68D 68F 68G 68H

68B 68D 68F 68G 68H

68B 68D 68F

8G H

OV-1B

104.40X1.4 = 146.16- 41.72X1.4 = 58.41 - 69.60X1.4= 97.44-

215.76X1.4 = 302.06 - 34.80X1.4= 48.72-

OV-1C/D

76.56X1.4 = 107.18- 34.80X1.4 = 48.72 41.72X1.4 = 58.41

222.72X1.4 = 311.81 ■ 76.56X1.4 = 107.18

U-21A

35.52X1.4= 49.73 35.52X1.4 = 49.73 71.04X1.4 = 99.46

213.12X1.4 = 298.37 35.52X1.4= 49.73

.07

.05

.02

.07

.02

.06

.02

.04

.12

.02

.04

.02

.02

.12

.04

.02

.02

.04

.12

.02

.07

.05

.01

.07 .01

.05

.02

.04

.11

.02

.04

.02

.02

.12

.04

.02

.02

.04

.11

.02

2-153

FM 101-20

# AVUM TI’s

2,500 AH-1G/S

67Y3 358.80x1.40 = 502.32 + .20

UH-1B/C/M

67N3 310.20 x 1.40 = 4 34.28 -s- .17

UH-1D/H

67N3 483.48 x 1.40 = 676.87 -s- .27

OH-6A

67V3 285.60x1.40 = 399.84 + .16

OH-58A

67V3 285.60x1.40 = 3 99.84 H- je

CH-47A/B/C

67U3 1,412.88 x 14.0 = 1,978.03 -5- .79

CH-54A/B

67X3 1,135.20 x 1.40 = 1,589.28 .64

U-21

67G3 328.56x1.40 = 459.98 -â- .18

OV-1B/C/D

67G3 368.88x1.40 = 516.43 -f- 21

2,700

.19

.16

.25

.15

.15

.73

.59

.17

2-154

FM 101-20

2,700

OH-6A

67V 465.12x1.4 = 651.17 68B 65.28x1.4= 91.39 68D 106.08x1.4 = 148.51 68F 24.48 x 1.4 = 34.27 68G 163.20x1.4 = 228.48

.24

.03

.06

.01

.08

I

OH-58A

67V 465.11 x 1.4 = 651.15 -s- .24 68B 326.40 x 1.4 = 456.96 + .17 68D 48.96 x 1.4 = 68.54 -s- .03 68F 24.48x1.4 = 34.27 -*- .01 68G 236.64 x 1.4 = 331.30 + .12 68H 16.32x1.4 = 22.85 -*- .01

UH-1B/C/M

67N 495.00 x 1.4 = 693.00 + 68B 165.00 x 1.4 = 231.00 -i- 68D 105.60 x 1.4 = 147.84 68F 19.80x1.4 = 27.72 + 68G 171.60x1.4 = 240.24 + 68H 13.20x1.4= 18.48 +

UH-1D/H

67N 616.20 x 14. = 862.68 + 68B 189.60 x 1.4 = 265.44 + 68D 151.68 x 1.4 = 212.35 + 68F 28.44x1.4= 39.82 + 68G 218.04 x 1.4 = 305.26 + 68H 9.48x1.4= 13.27 +

OV-1B

67G 508.08 x 1.4 = 711.31 + .26 68B 104.40 x 1.4 = 146.16 + .05 68D 13.92x1.4= 19.49+ .01 68F 6.96x1.4= 9.74+ .01 68G 334.08 x 1.4 = 467.71 + .17 68H 6.96x1.4= 9.74+ .01

.10

.08

.01

.11

.01

.09

.05

.01

.09

.01

# 2-155

;

FM 101-20

67Y3

67N3

67N3

67V3

67V3

67U3

67X3

67G3

67G3

AVIM TI’S

AH-1G/S 93.60x1.40 = 131.04-i- UH-IB/C/M

132.00 X 1.40 = 184.80 UH-1D/H. 142.20x1.40 = 199.08-5- OH-6A 65.28 x 1.40 = 91.39 H- OH-58A 65.28 x 1.40 = 91.39 -j- CH-47A/B/C 313.20 x 1.40 = 434.48 -f- CH-54A/B 196.08 x 1.40 = 274.51 -f- U-21 53.28 x 1.40 = 74.59 -h

OV-1B/C/D 97.44 x 1.40 = 136.42 -r-

2,700

.05

.07

.07

.03

.03

.16

.10

.03

.05

# 2-156

FM 101-20

CHAPTER 3

PERSONNEL REQUIREMENTS

Section I. OFFICER/WARRANT OFFICER AVIATION PERSONNEL REQUIREMENTS

3-1. Officer/Warrant Officer Requirements.

AR 570-1 contains criteria for, and lists positions where commissioned officers are authorized. Under these criteria, positions entailing essential command, staff, or supervisory functions for which an officer is especially required are so designated. All other positions are designated as warrant officer.

units will be manned with pilots and copilots to give the unit a sustained operational capability. Dual control aircraft assigned in certain indirect support categories may not require copilots unless flight must be performed under instrument conditions.

3-2. Cockpit Seat Fill Requirements.

Cockpit seat-fill requirements vary with the type of aircraft and the mission of the unit. At least the minimum crew complement prescribed in the operations handbook for a particular aircraft is authorized except for proficiency, contractor operated, and maintenance float aircraft for which no Army aviators are programmed. In general, dual control aircraft in combat, combat support units, and indirect support

i

3-1

FM 101-20

Section IL ENLISTED AVIATION MAINTENANCE PERSONNEL REQUIREMENTS

3-3. Enlisted Personnel Requirements.

a. AR570-2 provides staff officers and aircraft maintenance officers with uniform guidance to accomplish the following:

nance required for its continued serviceability. The relationship is termed man-hour per flight-hour ratio (MH/FH) and prevails in both user and support level maintenance. The ratio varies by type and model of aircraft, depending on aircraft size and complexity.

( 1 ) Evaluate manpower requirements for TOE/TD units as pertains to user and support maintenance activities.

(2) Determine manpower requirements in connection with procurement of aircraft maintenance services.

b. A relationship exists between the flying hours accumulated on aircraft and the man-hours of mainte-

3-2 J

FM 101-20

3-4. Enlisted MOS Applicable to Aircraft Types.

Current MOS Description

Category

AVUM AVIM Aircraft

Applicable

26E 26K

26M 26N 35K 35L

35M

35P 35R 41G

67G

67N 67T 67U 67V 67W 67X 67Y 67Z 68B 68D 68F 68G 68H 68J 68K 68M

Aerial Surveillance Sensor Repairer Aerial Electronic Warning/Defense

Equipment Repairer Aerial Surveillance Radar Repairer Aerial Surveillance Infrared Repairer Avionic Mechanic Avionic Communications Equipment

Repairer Avionic Navigation and Flight Control

Equipment Repairer Avionic Equipment Maintenance Supervisor Avionic Special Equipment Repairer Aerial Surveillance Photographic

Equipment Repairer Airplane Repairer

Utility Helicopter Repairer Tactical Transport Helicopter Repairer Medium Helicopter Repairer Observation/Scout Helicopter Repairer Aircraft Quality Control Supervisor Heavy Lift Helicopter Repairer Attack Helicopter Repairer Aircraft Maintenance Senior Sergeant Aircraft Powerplant Repairer Aircraft Powertrain Repairer Aircraft Electrician Aircraft Structural Repairer Aircraft Pneudraulics Repairer Helicopter Missile Systems Repairer Aircraft Component Repair Supervisor Helicopter Weapon Systems Repairer

X X X X X X X X X X X X X X

X X

X X X X

X X X

X X X X X X X X X X X X X X X X

OV-1D All

OV-1B OV-1C All All

All

All All. OV-ÏB/C

U-8, U-21,OV-l (series)

UH-1 (series) UH-60A CH-47 (series) OH-6A, OH-58 (series) All CH-54 (series) AH-1 (series) All All All All All All All RW All All RW

REFERENCE: CMF28and67,AR611-201.

NOTE: 1. MOS 67G has been tentatively identified as the Remotely Piloted Vehicle Repairer. 2. Contract maintenance is utilized to support the C-12A, however, MOS 67G may be utilized as a

flying crew chief.

3. MOS 67Y is currently being utilized for planning purposes during Phase II of the YAH-64A development program. Determination will be made at the end of Phase II relative to the need for the AH-64A.

Source: DRDAV-EON(2)

>3

i

• • • • • Section I. ARMY AIRCRAFT DIRECT COSTS PER FLYING HOUR (FY 78)

4-1. Costs Per Flying Hour (Standard Rate Cost Comparison • Army Administrative Versus Commercial).

Type Aircraft Field OMA Parts POL

Civilian jj Field Labor

Crewmen^] Hourly Per Diem

Cost 3J Comparison Rates

Reimbursement Rates For DOD & Non-DOD Users

Fixed Wing C-12A OV-1D RU-21 T-42 U-8F U-21A/G U-21F

Rotary Wing AH-1G AH-1S CH-47A CH-47B CH-47C

CH-54A CH-54B OH-6A OH-58A UH-1H

52 117

43 33 33 34 34

155 ¡& 215 318 318 318

336 336

38 38 59

47 85 50 26 28 50 55

49 51

148 158 198

180 170

9 11 45

<■>

79 54 41 41 41 37 37

75 95 97 95 88

116 116

20 19 28

22 15 22 15 22 22 22

15 ! > 15 29 29 29

29 29 15 15 22

APA Spares and Hourly

Depot Costs Rate

14 78 21 9 9

20 23

51 93

335 345 345

501 441

20 26 38

214 348 177 124 133 163 166

345 469 937 945 978

1102 1092

102 107 192

270 452 229 146 155 212 208

419 P’ 550

1164 1172 1205

1430 1420

126 132 257

322 578 347 254 278 313 309

709 JfiP 901

2036 2046 2081

2349 2338

294 301 508

CH

AP

TE

R 4

CO

ST

S

-b

lb

4-1. Costs Per Flying Hour (Standard Rate Cost Comparison ■ Army Administrative Versus Commercial (cont).

U If maintenance is performed by military personnel, or shared with civilian labor, civilian field labor rates should be prorated.

2/ Intra-Army rates have been revised by adding an hourly per diem factor for crewmen.

JL/ Cost comparison rates to be utilized for Army administrative air versus commercial air travel justification as required by AR 310-34 and AR 95-1. These rates include civilian labor, crewmen per diem plus APA replenishment spares and depot overhaul costs.

NOTE: Major commands have the authority to reprogram these rates when the situation dictates, i.e., due to contract maintenance, geographical location or special missions. When this situation occurs and it is determined that MACOM flying hour costs exceed the DA standard cost rate, it is most important that this information be transmitted to HQDA for updating data.

Source: DA COMPT (DACA-CA) AUTOVON 225-3568

FM 101-20

4-2. Costs per Flying Hour.

FIXED WING

Field \J

OMA Parts

Field 2]

Labor i;

POL

PEMA 3/

Parts

Depot 4/

OMA Parts

Depot 4/

Labor

Estimated Total FH Cost

OV-1 U-l UrlO U-21/RU-21 T-41 T-42 C12A UV-18A

ROTARY WING OH-6 OH-58 UH-1 AH-1 CH-47 CH-54 UH-60 YAH-64

$117 33

24

33 N/A

$ 38 38 59

155 318 336

$ 54 41

37

41

$ 20 19 28 75 88

116

$ 84 28

55

26 47

? 9 11 45 49

198 180

$24 1

1

1

0 3 3

20 63 65

$ 70 20

25

20

$ 23 25 48 52

244 323

$ 88 10

34

10

$ 21 21 52 53

265 381

$ 437 133

186

131

$ 111 117 235 404

1176 1401

1/ Program 2 costs per flying hour.

2/ MPA (MMH) costs per flying houi.

3/ PEMA costs per flying hour. Consists of PEMA II recurring repair parts.

4/ Program 7 costs p£r flying hour. Includes airframe and component overhaul costs. Airframe overhaul costs are based on 5-year overhaul cycle and flying hour program for TOE aircraft.

Note: The.factors above change frequently and should be used for planning only. Official flying hour costs for reimbursement

claims are developed by the Department of the Army Comptroller. Costs are in FY 78 dollars

Source: DA Compt (DACA)

FM 101-20

Section II.

4-3. Rotary Wing Unit Price.

AIRCRAFT UNIT FLYAWAY COSTS

HELICOPTER NATIONAL STOCK

NUMBER LINE ITEM

NUMBER TYPE STANDARD

PRICE*

AH-1G U TH-1G 2J CHAI A

CH-47B

CH-47C

YCH-47D

CH-54A 3/

CH-54B

OH-6A

OH-5 8 A

OH-58C

UH-1B

UH-lC

UH-1D

UH-1V

UH-1H

EH-1H

UH-1M

EH-1X

TH-55A

AH-1S UH-60A YAH-64A

1520-00999-9821 1520-00804-3635 1520-00633-6836

1520-00990-2941

1520-00871-7308

1520-00964-9601

1520-00113-5776

1520-00918-1523

1520-00169-7137

1520-01020-4216

1520-00713-9912

1520-00997-8862

1520-00859-2670

1520-01043-4949

1520-00087-7637

1520-00368-8442

1520-00809-2631

1520-01042-9396

1520-00758-0289

1520^00504-9112 1520-0135-0266

K29660 K29762 K30378

K30383

K30449

Z33490

K30515

K30516

K30645

K31042

Z33527

K31749

K31767

K31786

K31795^

K30548

K31804

H30829

K31153

K29694 K32293 Z33149

Attack Trainer Cargo Transport

Cargo Transport

Cargo Transport

Cargo Transport

Cargo Transport

Cargo Transport

Observation

Observation

Observation

Utility

Utility

Utility

Utility/Med Evac

Utility

Utility/Quick Fix

Utility

Utility/Quick Fix

Primary Trainer

Attack Utility Attack

509,833 531,679 990,717

1,063,448

3,223,625

2,660,828

2,817,371

125,821

144,722

201,898

244,760

224,415

237,504

618.055

618.055

1.920.000

247,758

1.920.000

35,590

1,537,000 4/ 2,282,200

y

"■Published in DA Supply Bulletin 700-20, Army Adopted/Other Selected Items and List of Reportable Items. Price includes avionics and $1,500 first destination transportation charges. Excludes armament systems except where annotated. (Refer to chapter 2.

\J Includes estimate of average cost of armament, $69,000. 2} Includes estimate of average cost of armament, $58,242. 3/ Includes $ 13,000 ground equipment. 4y Represents average lost of total new production/modemized AH-1S aircraft

N OTE : Aircraft type classified contingency or obsolete not included.

Source: DARCOM PM’s TSARCOM RPO’s & PM’s

4-4 j

FM 101-20

4-4. Fixed Wing Unit Price.

AIRCRAFT NATIONAL STOCK

NUMBER LINE ITEM

NUMBER TYPE STANDARD

PRICE*

U-8D

U-8F

U-8G

RU-8D

C-12A

U-10A

U-21A

U-21F

U-21G

RU-21A

RU-21B

RU-21C

RU-21D

RU-21H

RU-21J

0V-1B

0V-1C

0V-1D

RV-1D

T41B

T-42A UV-18A

1510-00574-7938

1510-00701-2233

1510-00912-4084

1510-00945-9998

1510-01005-5461

1510-00964-9780

1510-00933-8223

1510-00169-0295

1510-00140-1627

1510-00587-3375

1510-00878-4338

1510-00878-4336

1510-00804-3641

1510-00394-3320

1520-00124-0914

1510-00715-9379

1510-00715-9380

1510-00869-3654

1 510-00368-8440

1510-00929-1012

1510-00872-7908 1510-01011-1462

A30721

A30821

A30831

A30465

A29676

A30971

A30946

A30951

A30953

A30582

A30583

A30584

A30585

A30591

Z04615 A30221

A30271

A30296

A30444

A30053

A30596 A30989

Utility

Utility

Utility

Reconnaissance Utility

Utility

Utility STOL

Utility

Utility

Utility







Observation /Surveillance



Observation/Surveillance

Trainer, Flight

Trainer, Instrument

Utility

115.250

144,593

114,687

295.250

680,883

55,824

348,844

494,800

391,218

587.004

1,257,811

1,259,760

875.004

1,501,200

1,817,888

976,437

1,058,540

2,033,066

2,886,664

16,200

102,907

714,945

Published in DA Supply Bulletin 700-20, Army Adopted/Other Selected Items and List of Reportable Items. Price includes avionics and $1,500 first destination transportation charges. Excludes armament systems (Refer to chapter 2).

NOTE : Aircraft type classified contingency or obsolete not included.

Source: DARCOM PM’s TSARCOM RPO’s & PM's

4-5

FM 101-20

Section III. AVIONICS COSTS

4-5. Avionics Estimated Maintenance Cost Factors.

To obtain current data such as labor costs or parts costs on avionics equipment or'systems cont; CERCOM (DRSEL-ME-E ) AUTOVON 992-1685.

Source: CERCOM (DRSEL-ME-E)

Section IV. ARMAMENT COSTS

4-6. Airborne Armament Maintenance Costs.

To obtain current labor and parts costs on aircraft/weapon subsystems contact DRSAR-MAS-SS, AUTOVON 793-5668.

Source: DRSAR-MAS-SS

4-6 j

FM 101-20

CHAPTER 5

RESEARCH AND DEVELOPMENT OF MATERIEL

Army aviation research and development is conducted on aircraft systems and in areas not directly related to specific aircraft systems. Research not directly related to aircraft systems includes low speed aerodynamics, structures, and propulsion. Exploratory development is conducted in such areas as area fluid dynamics, aeromechanics, flight dynamics, flight loads, aircraft structures and composite materials, power devices, propulsion components, aircraft survivability, aircraft ground support equipment, reliability/maintainability, avionics technology, and aircraft weapons.

5-1. General.

a. Research aircraft are procured in limited quantities to evaluate concepts during the Research, Exploratory Development and Advanced Development phases of the R&D cycle.

b. Development aircraft systems are aircraft systems proposed for operational use to replace or complement current Army aircraft systems.

5-2. Development Aircraft Systems.

The following development aircraft systems are in order of priority.

5-3. YAH-64A (AAH). i

The AAH is a twin engine rotary wing aircraft designed as a stable, manned aerial weapons system. The AAH will become the primary attack helicopter and will be complemented by the AH-1 series attack helicopter.

5-1

FM 101-20

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Figure 5-1. Advanced Attack Helicopter (AAH) Hughes Model - YAH-64)

5-2

Figu

re 5-2. YA

H-64A

(AA

H)

DIMENSIONS

Rotor Dia 48.0 Ft Length:

Static Operating

Fuselage Span (Max

Lateral) 17.17 Ft Height 12.57 Ft. Tread Rotor Gnl Clearance:

(Static)

48.00 FT DIA

a 10.5 FT <5 17.17 FT

u 12.57 FT

8.58 FT DIA

V

11.88 FT 10.87 FT

n- o o

47.74 FT

57.62 FT

cn ¿a

FM

101-20

en 5-4. YÂH-64A (AAH) Characteristics.


No. and Model (2)T700-GE-700 Mfr General Electric Engine Spec. No DARCOM-CP-

2222-02000B Type Free Power Turbine Reduction Gear Ratio 72.42:1 Tail Pipe Fixed Area Augmentation None

ENGINE RATINGS

Intermediate 1543 SL/STD Max Continuous 1251 SL/STD


AIRFRAME:

NOT AVAILABLE

ENGINE:

Advanced Attack Helicopter (AAH)

The YAH-64A is being developed primarily for destruc- tion of armored vehicles, but is capable of defeating a wide range of other targets. It will provide direct aerial fires as an integral element of the ground units and will be responsive around the clock and under adverse weather conditions. It will contribute highly mobile, effective and accurate anti-armor firepower with the hellfire laser guided anti-armor missile, 30mm chain gun and 2.75 inch rockets. The AAH is equipped with an Integrated Target Acquisi- tion and Designation System (TADS) and a Pilot’s Night Vision System (PNVS). The aircraft is designed to survive against current and future enemy threats on the battle- field.

DEVELOPMENT

Date of contract jun 1973 First flight (similar aircraft) Mar 1975 First aeft delivered (Production) Dec 1982

FEATURES

Not Available

PERSONNEL

Pilot Co-Pilot/Gunner.

LOADING

Empty Basic Design Combat (Primary)

(Max Alt) (Ferry)

LB.

10,268 14,660 13.825 13.825 17,650 18,500

FUEL AND OIL

Fuel: Grade JP 4/5 Spec, MIL-T-5624J No. tanks 2 Location Fuselage Qty 365.2 Gal Usable

Oil: Spec MIL-L-7808G/

MIL-L-23699B No. tanks 2 Location Integral w/

Engine Qty 3.40 Gal

AVIONICS / ARMAMENT

Refer to chapter 2.

FLYAWAY COSTS / NSN

NSN — Not Available Lin Z33149 Costs — Not Aval

PM

10

1-2

0

5-5. Loading and Performance - Typical Mission YAH-64A

Conditions Primary Mission

Mission I

Mission II

Mission III

Mission IV

Ferry Mission

Mission Gross Weight (Take Off) Payload (Expendable Ordnance)

HELLFIRE 2.75” Rockets 30MM

Fuel (Usable) Vertical Rate of Climb OGE @ 4000 ft,

95°F, 95% IRP Rate of Climb @ 80 kts, 4000 ft, 95°F,

IRP Cruise Speed @ 4000 ft, 95°F, MCP

Endurance @ 4000 ft, 95°F

Hover Ceiling OGE 95#F, 95% IRP

Hover Ceiling IGE 95°F, 95% IRP Service Ceiling Standard Day, IRP

Service Ceiling Single Engine, Standard Day, IRP

Service Ceiling Single Engine, 95°F. IRP

Ferry Range

(lbs)

(Ibs/no) (Ibs/no) (lbs/no) (lbs)

(FPM)

(FPM) (KTAS)

(Hrs)

(Ft)

(Ft) (Ft)

(Ft)

(Ft)

(NM)

13825

704/8

247/320 1542

880

2480 146 1.83

6160

8000*

> 20000****

11500****

5600****

14202

704/8

616/800 1550

625

2330 145 1.83

5460

8000*

>20000****

15430

1408/16

760/986 1542

<0

138 1.70

3300

6140

15430

704/8 1072/38 482/626 1542

<0

139 1.68

3300

6140

15430

2143/76 204/265 1542

<0

139 1.68

3300

6140

10750 ****

4900 ****

CONDITIONS Alternate Mission

IA

Alternate Mission

IIA

Alternate Mission

IIIA

Alternate Mission

IVA

18500

6914**

<0

<0

1400

820***

Alternate Mission

VA

OI

Ol

Mission Gross Weight (Take Off) (lbs) Payload (Expendable Ordnance)

Hellfire (lbs/no) 2.75” Rockets (lbs/no) 30MM (lbs/no)

Fuel (Full Usable) (lbs) Endurance @ Sea Level, Std. Day (hrs)

15026 same as above

2374 2.61

16262 same as above

2374 2.51

16262 same as above

2374 2.53

16262 same as above

2374 2.53

16982

0 2143/76 924/1200 2374 2.50

*

**

***

***

Engine Operating Limit - 8000 ft, 95°F With External Fuel Tanks With 20 Knot Headwind At the Above Mission Gross Weights

FM 101-20

FM 101*20

5-6. Performance Notes, YAH-64A (AAH).

Formula: Primary Mission — Entire mission performed at 4000 ft, 95 F, 8 minutes at maximum continuous power, 30 minutes at 0-40 KTAS @ DGW*, 12 minutes at 80-100 KTAS <8> DGW*. 5 minutes at 150 KTAS © DGW, 25 minutes HOGE © DGW*, 30 minutes reserve at max range speed © DGW minus expendable ordnance minus fuel consumed.

•Computed Vi at DGW (mission gross weight) and Vi at DGW less Vt the expendable ordnance payload.

Formula: Alternate Mission I — Same as Primary Mission.

Formula: Alternate Mission II — Same as Primary Mission, except time at 80-100 KTAS is 4.2 minutes.

Formula: Alternate Mission III — Same as Primary Mission, except time at 80-100 KTAS is 2.6 minutes.

Formula: Alternate Mission IV — Same as Primary Mission, except time at 80-100 KTAS is 2.8 minutes.

Formula: Ferry Mission — Auxiliary fuel tanks utilized. 20 knot headwind. A 45 minute fuel reserve at max range speed shall be provided for flights up to 3 hrs in length. For flights over 3 hrs, reserve shall be increased by 10% of the additional fuel at the airspeed and headwind required above. 2 minutes at MCP shall be allowed for warm-up and take off. The mission shall be performed at standard day conditions with takeoff at sea level.

Formula: Alternate Mission IA — Entire mission performed at sea level standard day conditions, 8 minutes at maximum continuous power, 25 minutes HOGE © AGW*, 30 minutes 0-40KTAS © AGW*, 21.4 minutes at 150 KTAS @ AGW, 30 minutes at maximum endurance speed © AGW* 12 minutes 80-100 KTAS © AGW*, 30 minutes reserve at maximum range speed @ AGW minus expendable ordnance minus fuel consumed. •Computed Vt at AGW (sea level mission gross weight) and Vi at AGW less Vi the expendable ordnance payload.

Formula: Alternate Mission HA — Same as IA, except time @ 150KTAS is 15.6 minutes.

Formula: Alternate Mission IIIA — Same as IA, except time © 150 KTAS is 16.9 minutes.

Formula: Alternate Mission IVA — Same as I A, except time @150 KTAS is 16.9 minutes.

Formula: Alternate Mission VA — Same as IA, except time @150 KTAS is 15.1 minutes.

Performance Reference: System Specification AMC-SS-AAH-H10000A, YAH-64 Phase 2 Advanced Attack Helicopter.

Source: DRCPM-AAH-LM (2)

l 5-6

FM 101-20 r 5-7. Remotely Piloted Vehicle (RPV).

a. The RPV system is designed to provide realtime target acquisition and combat information beyond line of sight of its supported ground forces. The system has the capability to detect, recognize', and identify targets and assist artillery engagement out to 20KM forward of the line of contact (LC). Combat effectiveness will be increased especially against cold, non-moving, non-emitting targets while reducing the exposure of manned aircraft of the enemy. The system has the ability to perform airborne target acquisition and location, adjustment of field artillery fire control, laser designation for all tri-service precision guided munitions, reconnaissance missions, and damage assessment. The airframe will be a fixed wingtype with an air-cooled, two cylinder, two stroke engine

developing!,-approximately 20-25 horsepower propeller: drivehr •

RPV milestone schedule and illustration will be made available following, award of the full scale engineering contract.

Source: DRDAV-RP

i 5-7

!

i

FM 101-20

APPENDIX A

REFERENCES

ARMY REGULATIONS (AR) (DA REG 310-1)

70-50 Designating and Naming Military Aircraft, Rockets, and Guided MissUes.

95-70 Army Aviation Planning Manual.

310-50 Authorized Abbreviations and Brevity Codes. s •

310-25 Dictionary of United States Army Terms.

570-2 Organization and Equipment Authorization Tables - Personnel.

611-201 Enlisted Career Management Fields and Military Occupational Specialties.

750-1 Army Materiel Maintenance Concepts and Policies.

FIELD MANUALS (FM) DA PAMP 310-5)

1-100 Army Aviation Utilization.

1-105 Army Aviation Techniques and Procedures.

21-5 Military Training Management.

21-6 How to Prepare and Conduct Military Training.

21-30 Military Symbols.

21-60 Visual Signals.

55-15 Transportation Reference Data.

55-40 Army Combat Service Support Air Transport Operations.

57-35 Airmobile Operations.

101-10 Staff Officers’ Field Manual: Organization, Technical, and Logistical Data

(Part I — Unclassified).

TECHNICAL MANUALS (TM) (DA PAMP 310-4)

55-450-8 Air Transport of Supplies and Equipment: External-Transport Procedures.

55-450 series Air Transport of Supplies and Equipment: Internal-Transport Procedures.

A-1

FM 101-20

APPENDIX A (CONT.)

55-450-15 Air Movement of Troops and Equipment (Non-Tactical).

SUPPLY BULLETIN(S)

SB 700-10

yr /v° Army Adopted/Other Selected Items S* List of Reportable Items.

A-2

FM 101-20

INDEX

M156 Authorized aircraft designations Avionics and surveillance equipment

configurations Basic annual flying hour planning

factors Basis of issue Standard aircraft characteristics/

performance AH-1G/TH-1G (Hueycorbra) AH-IS(MOD) AH-IS (PROD) AH-IS(ECAS) C-12A (Huron) CH-47 A (Chinook) CH-47B (Chinook) CH-47C (Chinook) YCH-47D (Chinook) CH-54 A (Tar he) CH-54B(Tarhe) OH-6A(Cayuse) OH-58A (Kiowa) OH-58C (Kiowa) OV-IB (Mohawk) O V- 1C (Mohawk) OV - ID (Mohawk) RU-21B/C(Ute) RU-21D(Ute) RU-21H(Ute) RU-21J T-41B (Mescalero) T-42 A (Cochise) TH-55A(Osage) U-8D/G (Seminole) U-8F (Seminole) U-10A (Helio-Courier) U-21A/C and RU-21A(Ute) U-21F(Ute) UH- IB (Iroquois) UH- 1C (Iroquois) UH-1M (Iroquois) UH- ID (Iroquois) UH- 1H (Iroquois) UH-1V EH-1H EH-1X

Aircraft shipment processing time Aircraft armament Aircraft armament application Aircraft armor

AH-1G/S and TH-1G

Page Page

2-94 CH-47 2-116 1- 7 CH-54A 2-118

OH-6A 2-119 2- 2 OV-1 2-121

UH-1 Series 2-120 1-11 Aircraft armor systems 2-112

1-2 Aircraft authorization 1-1 Aircraft designation iv Aircraft inspections 2-135

1-17 Aircraft armament subsystem 1-21 rockets 2-110 1-23 Aircraft type classification viii 1-26 Aircraft armament subsystems

1-114 ammunition 2-105 1-32 Aviation intermediate maintenance 1-35 support units 2-146 1-39 AH-1 2-2 1-44 C-12A 2-34 1-50 CH-47 2-7 1-53 CH-54 2-13 1-59 OH-6A 2-17 1-65 OH-58 2-20 1-69 T-41B 2-45

1-119 T-42A 2-47 1-122 TH-55A 2-24 1-128 U-8 2-49 1-171 U-10A 2-53 1-163 U-21/RU-21 2-55 1-174 UH-1 2-25 1-177 UH-60A 2-30 1-137 - UV-18 2-61 1-141 ■ Armament subsystems

1-73 HMMS 2-104 1-145 M5 2-83 1-151 M18A1 2-66 1-157 M21 2-88 1-162 M22 2-91 1-168 ; M23 2-100

1-77 M24 2-76 1-83 M27 2-80 1-86. M28A1 2-69

.1-90 ; M28A2 2-67 1-94 M35 2-72 1- 99 M41 2-77

1-101 : M56 2-102 1- 103 M158A1 2-95 2- 124 M200A1 2-20

2- 63 M19 2-86 2-63 XM40 Not applicable

XM230EI 2-103 2-115 UH-60A 1-110

Index 1

FM 101-20

INDEX (con’t)

Page YAH-64A 5-4 RV-lD(Quick Look) 1-131 UV-18A 1-181

Cockpit seat fill requirements 3-1

Cost factors, avionics/armament estimated maintenance 4-6

Costs 4-1 Enlisted MOS applicable to

aircraft types 3-3 Fixed wing unit price 4-5 Fuel and oil consumption 2-138 Fuel and oil costs 2-136 Enlisted personnel requirements 3-2 Installations with capabilities

to perform aviation overhaul maintenance 2-149

Major components 2-1 Officer/warrant officer

requirements 3-1

Page Replacement factors 1-13 Remotely piloted vehicle

(RPV) : 5-7 Research and development of

materiel 5-1 Rotary wing unit price 4-4 Shop sets 2-138 Surface shipment 2-122 Surface shipment processing

time 2-123 Table of basis flying hour

planning factors 1-12 Test and test support aircraft 1-7 Tool kits 2-134 Tool sets 2-134 Total direct maintenance man-hours

per flight hour 2-141 Weight and cube for crated

shipment 2-127

Index 2

FM 101-20

By Order of the Secretary of the Army:

BERNARD W. ROGERS General, United States Army

Official: Chief of Staff

J. C. PENNINGTON Major General, United States Army

The Adjutant General

DISTRIBUTION : Active Army. ARNG. USAR: To be distributed in accordance with DA Form 12-11B,

requirements for US Army Aviation and Planning Manual.

»U.S. GOVERNMENT PRINTING OFFICE: 1979-603-028/1158

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